CJ
AAEC/E500
AUSTRALIAN ATOMIC ENERGY COMMISSION
RESEARCH ESTABLISHMENT
LUCAS HEIGHTS
A COMPILATION OF EXPERIMENTAL BURNOUT DATA FOR
AXIAL FLOW OF WATER IN ROD BUNDLES
by
A.G. CHAPMAN
G. CARRARD
February 1981
ISBN 0 642 59706 5
AUSTRALIAN ATOMIC ENERGY COMMISSION
RESEARCH ESTABLISHMENT
LUCAS HEIGHTS
A COMPILATION OF EXPERIMENTAL BURNOUT DATA FOR
AXIAL FLOW OF WATER IN ROD BUNDLES
A.G. CHAPMAN
G. CARRARD
ABSTRACT
A compilation has been made of burnout (critical heat flux) data from the
results of more than 12 000 tests on 321 electrically-heated, water-cooled
experimental assemblies each simulating, to some extent, the operating or
postulated accident conditions in the fuel elements of water-cooled nuclear
power reactors. The main geometric characteristics of the assemblies are
listed and references are given for the sources of information from which the
data were gathered.
Three practical uses of the compilation are surveys of parametric effects
on burnout, tests of burnout formulas, and optimisation of the empirical
coefficients in burnout formulas.
The report presents details and discusses aspects of
(Continued)
(i) the composition of the compilation in terms of various distinctive
features of the assemblies or tests;
(ii) the distributions of tests over the ranges of 20 important
variables; and
(iii) the distributions of tests over various fields of conditions
defined by variables considered simultaneously in pairs or sets of
four.
Details of the composition of the compilation and of the distributions of
tests are shown in tables and histograms. These provide information from
which a user of the compilation may assess the relevance of the data to areas
of particular interest.
The overall distribution of tests is discussed. It is concluded that
although the adequacy of the compilation to furnish significant samples of
data varies considerably with the location and delimitation of the area of
interest, a reasonable latitude in defining this area enables the compilation
to provide an effective data base.
National Library of Australia card number and ISBN 0 642 59706 5
The following descriptors have been selected from the INIS
Thesaurus to describe the subject content of this report for
information retrieval purposes. For further details please refer to
IAEA-INIS-12 (INIS: Manual for Indexing) and IAEA-INIS-13 (INIS:
Thesaurus) published in Vienna by the International Atomic Energy
Agency.
BURNOUT; FUEL ELEMENTS; REACTOR ACCIDENTS; SIMULATION; HEAT FLUX;
WATER-COOLED REACTORS; EXPERIMENTAL DATA
PREFACE
f A vital factor in the economy and safety of nuclear reactors is
Efficiency of heat transfer. When the reactor is cooled by a liquid, like
'most of those in use today, no aspect of heat transfer is more significant
than burnout, a physical phenomenon which limits the rate of efficient heat
removal from a surface by a boiling liquid. Burnout is the fundamental topic
of this report; it is therefore appropriate to state briefly what it is, how
the term is related to others in common use, and why it is necessary to study
it.
'Burnout' is the popular term for an effect produced by a local
transition in the mechanism of heat transfer which occurs at a surface cooled
by a boiling liquid when the heat flux attains a certain critical level,
dependent on the local conditions. At the transition, liquid ceases to wet
the surface and there is an abrupt and often substantial reduction in the
local heat transfer coefficient. In situations where the heat flux is
independent of the heat transfer coefficient, this produces an abrupt rise in
the temperature of the surface. The magnitude of the temperature rise depends
on the conditions; it may be enough to destroy a metal surface and hence the
effect is called 'burnout', whether or not the surface is damaged.
The term 'burnout' describes an effect which may be observed, but it does
not signify the nature of the transition or crisis that causes it. There are
different kinds of boiling crisis that result in burnout; generally the
nature of the crisis cannot be observed, but it may be surmised. On this
basis the term 'burnout' can be replaced by one of two more specific terms:
'Departure from nucleate boiling (DNB)' is a term denoting the crisis
that locally terminates a nucleate boiling process; this crisis is a common
cause of burnout when a coolant with low vapour content flows over a heated
sur face.
'Dryout' denotes a burnout that arises from the eventual disappearance of
a liquid film that flows along the heated surface when the coolant has a high
vapour content.
An older and more general term that is often preferred is:
'Critical heat flux (CHF)1 which denotes the heat flux at a boiling
crisis regardless of its effect. In a system in which the heat flux is
controlled, the effect is burnout, whereas in a system with surface
temperature control, the effect is the initiation of a limited phase of heat
transfer in which there is a progressive reduction of heat flux with
increasing surface temperature.
In water-cooled nuclear power reactors, the fuel is contained in long,
parallel, cylindrical rods arranged in regular arrays called 'rod bundles'.
The heat released in the fuel is transferred to water flowing axially through
the rod bundles at or near boiling conditions and the ability to predict the
burnout heat flux is essential, both for the avoidance of burnout under
operating conditions and for an assessment of the safety of the reactor system
under postulated accident conditions.
As a part of a varied program of research into safety assessment aspects
of water-cooled nuclear reactors, the AAEC's Research Establishment at Lucas
Heights has been investigating simple methods of predicting the burnout heat
flux in water-cooled rod bundles. One of the first requirements of the
investigation was the assembly of a bank of experimental data against which
theoretical predictions could be tested. This report is concerned solely with
a description of this data bank.
CONTENTS
1. INTRODUCTION 1
2. USES OF THE DATA COMPILATION 3
3. RULES FOR ADMISSION OF DATA 4
4. NAMING OF REVISIONS OF THE COMPILATION 5
5. DISTINCTIVE FEATURES OF THE TEST ASSEMBLIES AND TEST CONDITIONS 5
5.1 Rod Arrangement and Duct Shape 6
5.2 Distribution of Heat Flux 7
5.3 Phase Condition of the Coolant 8
5.4 Unusual or Abnormal Features of Tests 11
6. DISTRIBUTIONS OF THE TESTS OVER THE RANGES OF PRINCIPAL VARIABLES 11
6.1 Distributions with Respect to Single Variables 12
6.2 Distribution of Tests Over the Ranges of Two or More Variables
Considered Simultaneously 23
7. GENERAL DISCUSSION 25
8. CONCLUSIONS 6
9. ACKNOWLEDGEMENTS 27
10. REFERENCES 8
10.1 General 8
10.2 Sources of Published Data 29
11. NOTATION 38
12. GLOSSARY 40
13. ABBREVIATIONS USED IN THE TEXT 44
13.1 Laboratory Names and Locations and Number of Tests 44
13.2 Names of Reactor Concepts and Designs 45
CONTENTS (Continued)
Table 1 Compilations of Burnout Data for Axial Flow of 48
Water Through Rod Bundles and Annuli
Table 2A Main Characteristics of Test Assemblies 50
Table 2B Number and Range of Burnout Tests with Each Assembly 51
Table 2C Meanings of Symbols Used to Indicate Special Features 58
of Assemblies
Table 2D Grid or Rod Spacer Types and Reference Numbers 59
Table 3A Composition of the Data Bank in Respect of Rod 60
Arrangement
Table 3B Subdivision of Rod Arrangement Classes According to 60
Number of Rods
Table 3C Composition of the Data Bank in Respect of the Shape 61
of the Assembly Duct
Table 4A Composition of the Data Bank in Respect of Heat Flux 62
Distribution
Table 4B Subdivision of Tests with Axially Non-Uniform Heating 63
According to Flux Profile
Table 4C Distribution of Tests Between Assemblies with Unheated 63
and Heated Ducts
Table 5 Distribution of Burnout Tests According to Phase 64
Condition of the Coolant
Table 6A Composition of the Data Bank in Respect of Unusual or 65
Abnormal Features of the Test Assembly
Table 6B Numbers of Tests Associated with Individual Features 65
Tables Distribution of Tests Among Regions Defined by Equal 66-
7-17 Divisions of the Ranges of 2 Variables Considered 86
Simultaneously
Tables Distribution of Tests Among Regions Defined by 88-
18-26 Percentile Divisions of the Ranges of 2 Variables 96
Considered Simultaneously
Tables Distribution of Tests Among Regions Defined by 98-
27-31 Percentile Divisions of the Ranges of 4 Variables 105
Considered Simultaneously
CONTENTS (Continued)
Figure 1 Distribution of tests over the range of system 107
pressure
Figure 2 Distribution of tests over the range of coolant 108
mass flux
Figure 3 Distribution of tests over the range of coolant 109
quality at channel inlet
Figure 4 Distribution of tests over the range of coolant 110
bulk quality at burnout
Figure 5 Distribution of tests over the range of local 111
burnout heat flux
Figure 6 Distribution of tests over the range of number 112
of rods
Figure 7 Distribution of tests over the range of rod diameter 113
Figure 3 Distribution of tests over the range of rod 114
pitch:diameter ratio
Figure 9 Distribution of tests over the range of hydraulic 115
equivalent diameter
Figure 10 Distribution of tests over the range of heated 116
equivalent diameter
Figure 11 Distribution of tests over the range of 117
heated:wetted perimeter ratio
Figure 12 Distribution of tests over the range of heat flux 118
transverse form factor
Figure 13 Distribution of tests over the range of heat flux 119
axial form factor
Figure 14 Distribution of tests over the range of heated length 120
Figure 15 Distribution of tests over the ratio of heated length 121
to heated equivalent diameter
Figure 16 Distribution of tests over the range of boiling length 122
Figure 17 Distribution of tests over the ratio of boiling length 123
to heated equivalent diameter
Figure 18 Distribution of tests over the range of boiling 124
number x 1000
Figure 19 Distribution of tests over the range of Weber number 125
Figure 20 Distribution of tests over the range of liquid 126
Froude number
1. INTRODUCTION
The fundamental importance of the burnout phenomenon in nuclear
engineering has encouraged a search for theoretical explanations and there has
been some success in the analytical treatment of dryout in tubes and rod
bundles. However, extended study has so far failed to produce an adequate
theory of burnout in flow boiling that would permit accurate prediction of the
burnout heat flux in rod bundles. Investigators have therefore resorted to
empirical methods. Since the 1950s, many tens of thousands of tests have been
performed in laboratories around the world to measure burnout heat fluxes in
electrically-heated, water-cooled test channels of many different forms, with
many different conditions of the coolant.
At first, the aim was to derive a general empirical formula for the
prediction of burnout heat flux and some measure of success was achieved in
the cases of round tubes and annular ducts, the simplest forms of coolant
channel. Burnout is essentially a local event, however, and in complex flow
channels the internal variations of fluid condition determined by velocity,
temperature, and voidage distributions can have a significant effect on the
burnout heat flux. Since no terms have yet been found which express simply
and adequately the influences of such variations, there has been only limited
success in the derivation of a burnout formula for flow in rod bundles.
In more recent times, therefore, the aim of most burnout tests has been
to determine the burnout characteristics of particular rod bundle arrangements
directly, using full-scale models of either whole fuel element assemblies or
portions of them. These tests have been performed on specially made and
instrumented assemblies with electrically-heated rods simulating the fuel rods
of a nuclear reactor. In some cases, the rods have been heated non-uniformly
along their length, imitating to some degree the distribution of fission heat
release in a reactor fuel element. Large test rig installations have been
required to produce flow, pressure, and temperature conditions similar to
those of an operating reactor, and to provide sufficient rates of heat release
in the rods to cause burnout at these conditions which, of course, exceed the
normal rates of heat release in the actual fuel rods.
In the absence of an adequate theory, the accumulated results of these
tests are the only source of basic knowledge about burnout in rod bundles.
Not all of the results are freely available; large-scale burnout experiments
are very costly and many have been made during the development of commercial
designs of fuel element; consequently there is an unknown, but probably very
large, number of results which have not been published because they might
disclose proprietary information. The results that have been reported in
detail in the open literature, coming from a variety of sources and existing
for a variety of reasons, form a medley of data in which systematic variation
is confined to small ranges of a few variables. Nevertheless, they are
sufficient in number and diversity to provide an effective general reference
base of established burnout observations. This report describes, in detail, a
systematic compilation of these published experimental burnout data, augmented
by other data that have been made available to the authors. Only water test
data are included and the compilation is expressly of rod bundle data;
however, a limited amount of data for annular channels is admitted because
these channels may be regarded as extreme cases of a rod bundle.
?
From time to time, additional data become available and, if considered
admissible, these data are added to the data bank. The name BACE is used to
refer to the compilation in general; various revisions are denoted by
extensions to the name which indicate the date of revision. This is discussed
in more detail in Section 4. The version described in this report is BACE279C.
Several previous compilations of rod bundle and annulus burnout data have
been published. Table 1 gives brief particulars of these together with
details of BACE279C. At about the time of the Barnett [1968] compilation, an
unpublished computer file of burnout data was assembled at AEEW. A part of
this file, consisting of the results of 367 tests on 24 rod bundles, was
supplied to the authors and forms the nucleus of BACE.
In its current state, the compilation contains the results of 12 473
burnout tests. The data have been extracted from 91 reports of investigations
carried out in 24 laboratories in nine countries. All admissible rod bundle
data from sources named in the previous compilations (see Table 1) are
included (no details of Mironov's sources appear to have been published).
Location of the sources of early data was greatly assisted by published
summaries, such as those of Tong [1969, 1972] which list particulars of more
than 35 rod bundles and indicate the sources of data for 3148 tests, and
Hughes [1970a] which lists particulars of 36 rod bundles and the sources of
data for 1846 tests.
The system, structure, and format of the data records will be fully
described in a users' manual. In the following sections, the rules adopted as
the criteria for data admission are explained and the general features and
scope of the compilation are described. Because this report is a general
reference handbook for the BACE279C compilation, Sections 5 and 6 are quite
detailed. They may be omitted by the casual reader, but should help the
intending user who is interested in a particular aspect of the data.
Throughout this report, laboratories and reactor designs are referred to
by acronym or abbreviated name; these are identified in Section 13. Notation
and a glossary of terms are given in Sections 11 and 12 respectively.
References by author(s) name and date are listed in Section 10.1 and
references to tabulated sources of data are cited in numerical sequence in
Section 10.2.
2. USES OF THE DATA COMPILATION
Three main uses for the data compilation are envisaged.
(a) Surveys of parametric effects
Nominally constant values may be chosen for all but one of the principal
independent variables and data selected within limits set suitably close to
the nominal values. The resulting data subset contains information revealing
the isolated effect of the remaining independent variable upon the burnout
heat flux. Variables may be simple or compound, a compound variable being a
specific combination of simple variables.
(b) Tests of burnout formulas
Burnout test values of a variable may be compared with corresponding
values calculated from a burnout formula. A statistically significant number
of such comparisons indicates the accuracy of the formula within the range of
the data selected. If small ranges are chosen and these are varied
systematically, the influence of system conditions on the performance of the
formula may be determined.
(c) Optimisation of burnout formulas
The empirical coefficients of a burnout formula may be optimised by
methods of multiple regression using data sets generated from the compilation.
3. RULES FOR ADMISSION OF DATA
The following rules govern the admission of data -co the BACE compilation:
(a) The data must have been obtained from detailed descriptions of
water-cooled rod bundle or annul us assemblies, and from the
tabulated results of actual tests on these assemblies in which
burnout was detected. Data obtained by interpolation or scaled from
graphical presentations of results are not admitted.
(b) There must not be any doubt about the validity of the data founded
upon an objective assessment of the suitability of the test
apparatus or the method of conducting the test.
(c) There must be no clear indication that burnout was induced by flow
instability. A test result is not admitted if the measured burnout
power is significantly and singularly lower than that measured in
the same channel with substantially the same pressure and mass flux
but higher enthalpy at the inlet to the channel.
(d) The data admitted from any one test series must be self-consistent.
A test series is a number of tests performed on the same assembly
with systematic variation of any of the independent variables
governing the condition of the coolant. Graphical plots or
statistical analysis of the data must clearly indicate, to the
extent that is possible, a systematic relation between principal
dependent and independent variables. Results which are plainly
shown by the plots or analysis to be inconsistent with the main body
of data are discarded.
(e) Data from tests on assemblies with unusual or abnormal features
(such as an eccentric rod or rod bundle, a bowed rod, horizontal or
downward flow, or misalignment of rods) are admitted. A system of
labels is used to indicate the nature of the abnormality and permit
preferential selection of data.
(f) All available data from tests on rod bundle assemblies satisfying
the foregoing requirements are admitted without selection. A single
rod enclosed in a non-circular duct is classed as a rod bundle.
Data from tests on annular channels satisfying the foregoing
requirements may be admitted, provided that annular channels are not
disproportionately represented in the compilation. To ensure this,
no more than about 10 per cent of the tests providing data in the
compilation are to relate to annular channels. (This is about the
greatest proportion of tests relating to any one number of rods in
the BACE279C compilation and is roughly the same proportion as that
relating to assemblies of seven, nine, nineteen or thirty-seven
rods.)
4. NAMING OF REVISIONS OF THE COMPILATION
Revisions of the compilation are identified by adding to the generic name
(BACE) three characters indicating the date of revision and one character
indicating whether confidential data are included. The first of the three
characters specifies the month, the other two the year. The first nine months
of the year are indicated by the numerals 1 to 9, the last three by their
?Initial letttr. A final character C indicates that a compilation contains
some confidential data, a final U denotes a version from which confidential
data have been excluded. Thus, the name BACE279C identifies the state of the
confidential version of the BACE compilation in February 1979.
5. DISTINCTIVE FEATURES OF THE TEST ASSEMBLIES AND TEST CONDITIONS
A list of the test assemblies included in the compilation is given in
Table 2A. The entire data compilation which resides in a computer reference
volume is, of course, too large to be listed here. The list indicates the
sources of the data and summarises the main geometric characteristics of the
assemblies. The distribution of heat flux over the heated surfaces, which is
usually effected by varying the wall thickness, is regarded as a geometric
characteristic. A complementary list (Table 2B) shows the number of burnout
tests recorded for each assembly and the ranges of the principal test
conditions. In this compilation, the identity of a test assembly is
determined by the geometric characteristics; identical 'rebuilds1 are not
regarded as different assemblies, but an adjustment that effects a significant
change in a characteristic is generally regarded as creating a different
assembly. This explains the occurrence of numbers of very similar assemblies
in the list. When adjustments are numerous, however, it is not practical to
allocate separate identities to each modification and some assemblies have a
variable geometric characteristic. In these cases, separate entries for the
assembly are made in Tables 2A and 2B for groups of tests made with
significantly different average values of the variable characteristic.
To simplify description of the composition of the data bank, burnout
tests have been broadly classified according to various distinctive
characteristics of the assembly or test condition, namely (i) the form of rod
arrangement and duct shape, (ii) the distribution of heat flux, (ill) the
phase condition of the coolant, and (iv) the presence of unusual or abnormal
features. Each of these characteristics provides a different aspect from
which the composition of the data bank can be viewed. In the remarks which
follow, it is the composition of the data bank as a whole that is described.
This does not mean that the compilation is an indivisible body of data; it
may readily be subdivided, using computer sorting techniques, into subsets
with particular characteristics. Qualitative as well as quantitative
information is included in the data and many qualitative attributes such as
rod pitch arrangement, form and skew of axial heat flux profile, and the
nature of peculiarities may be identified for the purpose of sorting the data.
5.1 Rod Arrangement and Duct Shape
Table 3A shows the number of tests associated with various forms of rod
arrangement or array. As might be expected, the two largest classes,
accounting betvieen them for 70 per cent of the tests, are the circular pitch
and square pitch forms generally used in the fuel elements of water-cooled
nuclear power reactors of the pressure tube and pressure vessel types
respectively. Tests with circular pitch arrays outnumber those with square
pitch arrays in the ratio 3:2. This bias is due largely to the substantial
quantity of data for the former arrangement made available to the authors by
AEEW.
The third largest class, accounting for 19 per cent of the total number
of tests, contains tests performed on assemblies with rods arranged on an
equilateral triangular pitch, as is specified in the design of fuel elements
for the conceptual LWBR. One third of the tests included in this class were,
in fact, made in support of the LWBR program. Half of the tests in the
triangular pitch class were performed on bundles of three rods, an arrangement
commonly used in the small-scale tests of early research programs. In this
respect, the triangular pitch class contrasts strongly with the square pitch
class, in which only 8 per cent of the tests were performed on elementary rod
arrangements. The subject of rod number is treated more fully later in this
report but, since size is an important characteristic of arrays, the three
main classes of rod arrangement have been subdivided according to rod number.
The details are given in Table 3B.
Six rods spaced evenly around a central rod may be regarded as either a
circular pitch array or a triangular pitch array; such bundles are classed as
the former if the enclosing duct is circular in section and as the latter if
it is not circular. This classification, though logical, may not suit all
purposes and, therefore, the number of tests on 7-rod bundles included in the
circular pitch class is shown separately in Tables 3A and 3B.
The annular arrangement forms a small class because the number of annul us
tests included in the compilation has been deliberately restricted to avoid an
undue emphasis on single rod assemblies. However, in view of the relatively
small quantity of data that is available from tests with axially non-uniform
heat flux (in assemblies of any kind), a high proportion of the annul us data
selected for inclusion is from tests of this type.
A classification of the tests according to the shape of the duct
enclosing the rod bundle is given in Table 3C. All of the circular pitch
arrays, most of the 3-rod triangular pitch arrays, and some of the 4-rod
square pitch arrays are enclosed in ducts of circular cross-section. Annular
arrangements, of course, also fall into this class. The result is that 6U per
cent of the tests in the compilation are associated with circular ducts. The
remainder of the square pitch arrays are enclosed in ducts of rectangular
(mostly square) or cruciform cross-section. With the exception of the 3-rod
arrays, which have either circular or triangular ducts, triangular pitch
arrays are enclosed in ducts of hexagonal or parallelogrammatic cross-section.
Those single rods not in annular or simulated circular pitch arrangements are
enclosed in either square or hexagonal ducts.
5.2 Distribution of Heat Flux
A broad classification of the tests according to the distribution of heat
flux over the heated surfaces is given in Table 4A. Although the data are
fairly evenly divided between uniform and non-uniform distributions in the
radial direction, 87 per cent of the tests were performed on test assemblies
with rods heated uniformly along their length. The paucity of published
burnout data for axially non-uniform heat flux can be attributed to the high
8
cost of manufacturing and instrumenting the test assemblies, especially
multi-rod bundles. Not only have fewer experiments been performed on
assemblies with axially non-uniform heating, but a large proportion of the
results that have been obtained is classed as proprietary information and is
not freely available. It has already been mentioned, in connection with rod
arrangement, that the axially non-uniform heat flux component of the data bank
was reinforced by preferential selection of annulus tests. As a result,
experiments with annular arrangements contribute almost a quarter of the total
number of tests associated with axially non-uniform heat flux.
A large proportion of the axially non-uniform heat flux tests (95 per
cent) provide information about the axial position of the burnout point. In
about 2.5 per cent of the tests with axially uniform heat flux, burnout was
first detected at a point upstream of the end of the heated length; its
position is recorded in the data.
A further resolution of the axially non-uniform heat flux tests into
classes according to the form and skew of the axial flux profile is given in
Table 4B. Two-thirds of these tests are associated with profiles that are
symmetrical about the mid-length of the channel; these profiles generally
approximate a truncated cosine form. Among the remainder of the tests, those
with profiles skewed towards the channel exit outnumber those with skew
towards the inlet in the ratio of 5:2. Half of the latter were performed with
step flux profiles but, in general, the number of tests associated with step
or spike (i.e. 'hot patch1) profiles is small.
In a small proportion of the tests (see Table 4C), the duct enclosing the
rod or rod bundle was heated to simulate the effect of the surrounding rods in
a larger array. All of the tests with axially non-uniform heating of the duct
were performed on assemblies with single, uniformly-heated rods; about one
third were performed on an annular assembly with a truncated cosine
distribution of heat flux along the outer tube and the others were performed
on a one-rod simulation of a circular pitch array with heating applied to only
part of the length of the duct.
5.3 Phase Condition of the Coolant
In a large proportion (over 90 per cent) of the tests, the cooling water
entered the test channel in a subcooled condition, i.e. at a temperature below
saturation. In about one in seven cases, the average condition of the water
at the cross-section containing the burnout point was also subcooled. The
number of tests in each class is to be found in Table 5.
Burnout data from tests in which the coolant was admitted to the test
channel with a small degree of subcooling or as a two-phase mixture must be
used with discretion. It is well known that the presence of a compressible
medium, both upstream and downstream of a test channel which has a
sufficiently low pressure drop, enables flow oscillations to develop, inducing
burnout at a lower heat flux. The results of burnout tests may thus be
affected if there is surface or bulk boiling in the preheater, or if steam is
mixed with the water admitted to the test channel. The flow oscillation is
confined to the two-phase region and often escapes detection by the
instruments normally used in burnout tests. A high pressure drop tends to
inhibit flow oscillation and, in many of the reported tests with a steam-water
mixture at the test channel inlet, stable flow conditions were achieved by
placing a flow restriction just upstream of the test channel.
An endeavour has been made to exclude any data affected by flow
oscillation by the application of rule (c) (Section 3), but this rule is by no
means infallible. The stability of the flow cannot be inferred from the
presence or absence of an upstream flow restriction because the insertion of a
restriction is not always necessary, nor is it always sufficient, to produce
flow stability. Judgement on whether a result is affected by flow oscillation
rests entirely on a comparison of the result with others obtained in the same
series of tests. In some series, the range of coolant inlet condition
extended from a highly subcooled state, in which the results would not have
been affected, into a two-phase state, in which they might have been. In
these cases, affected results are easily recognised by a distinct lack of
consistency with the trend of the unaffected results, which is a regular
though not necessarily uniform decrease in burnout heat flux with increase in
inlet enthalpy at constant pressure and mass flow rate. There are other
series, however, in which all tests were performed with two-phase inlet
conditions and any of the results might have been affected; about one third of
the two-phase inlet tests included in the compilation are in this class.
In these cases, two methods have been used to single out affected data.
Firstly, if repeated tests have produced significantly different results, the
tests indicating the lower values of burnout heat flux have been excluded.
Secondly, an unsystematic reversal of the normal trend of burnout results is
considered to be a sign of premature burnout due to flow oscillation and a
10
test has been excluded if it indicates a singularly lower burnout power than
another test performed on the same assembly, at the same pressure and mass
flow rate, but with a significantly higher inlet enthalpy.
The procedures described above do not ensure the exclusion of all data
affected by flow oscillation. There are examples of data [ref. 42] which, in
isolation, present a normal trend, but which are known to be affected because
a repetition of the tests after the insertion of an upstream flow restriction
produced different results. Such checks have not been the general rule in
burnout experiments and, in some cases, affected data may not have been
recognised and may be included in the compilation. Attention must be drawn to
the fact that self-consistency of data is the only requirement that has been
imposed; no test of compatibility between sets of data from different sources
has been applied. Such a test might, of course, reveal an abnormality which
could be attributed to the effect of flow oscillation. However, it is left to
the user to make judgements of this kind. The authors have adhered to the
principle that data should not be excluded solely on the grounds of
nonconformity with the majority.
When the coolant is admitted as a two-phase mixture to a short test
assembly, or to one in which there is little of the mixing action which may be
provided by rod spacers, the burnout heat flux is affected by the distribution
of the phases at inlet to the assembly. This distribution depends upon the
methods of production and introduction of the mixture. The methods used in
the tests were as follows:
(i) Combination of slightly subcooled water and saturated or slightly
superheated steam in a mixing device designed to produce a uniform
suspension of droplets, or 'fog'.
(ii) Throttling of high-pressure, subcooled water or steam-water mixture
to produce a low quality steam-water mixture.
(iii) Partial evaporation of water in a once-through electric heater to
produce a flowing steam-water mixture.
(iv) Use of a flow diverter in a flowing steam-water mixture to
concentrate the flow (i.e. most of the water, since the liquid phase
is more effectively diverted) into the core or rod-filled section of
the test assembly.
11
(v) Injection of separate streams of subcooled water and superheated
steam into an inlet chamber of the test assembly, the water being
directed into the core of the assembly or sprayed onto unheated
leading extensions of the rods.
In the compilation, phase distribution is broadly classed and indicated
as uniform or non-uniform. Although only the first of the methods listed
above is likely to have mixed the phases thoroughly, the first three are
regarded as having produced uniform mixtures. The last two, by design,
produced non-uniform mixing. In all cases of non-uniform mixing, the water
was directed preferentially into the vicinity of the rods or onto their
surfaces. The results of tests on annular assemblies with non-uniformly mixed
two-phase inlet conditions [ref. 87] indicate an effect of the upstream
unheated rod length on the burnout heat flux; consequently, this length is
included in the data whenever the inlet phase distribution was non-uniform.
5.4 Unusual or Abnormal Features of Tests
More than 90 per cent of the tests were performed on assemblies of
nominally clean, smooth, straight, parallel rods arranged centrally within
vertical ducts and cooled by a forced upflow of water, or steam-water mixture.
The ranainder were performed on assemblies with unusual or abnormal features.
Unusual features include downflow, natural circulation, heavy water coolant,
converging rods, and horizontal arrangement of the assembly. Features which
are designated abnormal are those simulating possible defects in normal
assemblies and include a bowed rod, two rods touching, reduced clearance
between a rod and the duct wall, eccentric arrangement of the rod bundle in
the duct, misalignment of rods in a segmented bundle, partial blockage of a
coolant flow channel, and a deposit of crud on the rods.
The total number of tests having unusual or abnormal features is shown in
Table 6A and the numbers associated with each feature are given in Table 6B.
Unusual and abnormal features are indicated in the compilation and the user
may optionally include the associated data in a particular application.
6. DISTRIBUTIONS OF THE TESTS OVER THE RANGES OF PRINCIPAL VARIABLES
The manner in which the compiled data are distributed over the ranges of
the principal variables, each considered in isolation from the others, is
12
shown by a series of histograms in Figures 1 to 20. These figures show at a
glance the range and disposition of the data with respect to single variables;
however, the information they provide, although very useful, is of limited
value because no single variable has a dominating influence on burnout and, to
determine the relevance of the data to particular situations, it is necessary
to consider the distributions of several variables simultaneously. This has
been done for two and four variables; some multi-variable joint distributions
of the data are shown in Tables 7 to 31. There is no difficulty in using
these tables to determine the density of the data distribution in various
regions of the multi-variable field but, as displays of the overall character
of the distribution, they lack the simple clarity of histograms and require an
effort of visualisation that increases with the number of variables. Some
remarks about salient features of the data distribution are given in Section
6.1.
6.1 Distributions with Respect to Single Variables
Figures 1 to 5 are histograms showing the distribution of tests over the
ranges of principal coolant conditions and Figures 16 to 20 show distributions
over the ranges of variables tha/t are dependent on coolant conditions.
Because of the nature of the variables, these distributions tend to be
continuous although, for reasons which will be explained, this is hardly so in
the cases of pressure and mass flux. In contrast, the distributions of tests
over the ranges of quantifiable characteristics of the test assembly (Figures
6 to 15) are highly discontinuous. This is due to the fixed nature of the
variable within each assembly and the relatively small number of different
assemblies (321). In all of the figures, whatever characteristic is shown,
frequencies of occurrence are based on the number of tests (never the number
of assemblies) associated with each interval of the variable.
6.1.1 Pressure
Figure 1 shows the distribution of tests over the range of system
pressure. In some tests, the system pressure was measured at the test section
inlet, in others at the outlet; reports often fail to indicate clearly where
the measurement was made. In the absence of an indication, it has been
assumed that the pressure was measured at the test section outlet, which is
the normal position of burnout in an assembly with uniform axial distribution
of heat flux. The stated or assumed location of the point at which the system
pressure was measured is indicated in the data compilation but, because the
13
pressure drop in the test assembly was recorded in only a small proportion of
the tests (about 20 per cent), it is not possible to express the system
pressure at a common location. Unavoidably, therefore, inlet and outlet
pressures have been used without discrimination when determining the
distribution of tests over the range of system pressure. Whenever it could be
ascertained, the pressure at the test section outlet has been used., because
this was where the measurement was made in most of the low pressure tests; it
is in these tests that the difference between inlet and outlet pressure is
most significant.
System absolute pressures range in the compilation from 0.04 HPa (sub-
atmospheric) to 17.0 MPa. Tests at the lowest pressure were performed at ORNL
on a 7-rod bundle, 0.295 m in length (denoted in Tables 2A and 2B as assembly
number 181). Tests at the highest pressure were carried out at Columbia on
assembly number 244, a 16-rod bundle, 2.44 m in length, with a non-uniform
axial distribution of heat flux skewed towards the outlet. It has been the
usual practice, in those burnout experiments in which pressure was varied
systematically, to choose values which are multiples of either 100 psia or 1
MPa. Figure 1 distinctly shows the concentrations of tests at these standard
pressures, which include the more common design pressures for water-cooled
power reactors. The dominant peak between 6.8 and 7.0 MPa (nominally 1000
psia, a notional design pressure for boiling water reactors) represents 22 per
cent of the tests included in the compilation and reflects a general tendency
for a common pressure to be adopted in many early rod bundle experiments.
6.1.2 Mass flux
Coolant mass fluxes range in the compilation from 1.27 to 155712 1 ?
g s cm c; however, the mass flux exceeds 600 g s cm in only 2.4 per
cent of the tests. Tests at the lowest mass flux were carried but on assembly
number 181, as were those at the lowest pressure (see Section 6.1.1). The
highest mass flux associated with a multi-rod bundle is 680.8 g s cm ; it
was attained in a test performed at Hanford on assembly number 134, a
horizontal 19-rod wire-wrapped bundle 0.495 m in length. All higher values of
mass flux occur in annular assemblies; the highest was attained in tests
performed at SRL on assembly number A12 with heavy water flowing at a velocity
of 14.5 m s"1.
Systematic variation of mass flux has been common in burnout experiments
but, as with pressure variation, the usual practice has been to adhere to
14
standard intervals; Figure 2 shows distinct concentrations of tests at values612
of mass flux which are multiples of 0.5 x 10 Ib h ft . Under normal
operating conditions in water-cooled power reactors, the mass flux of the1 -2
coolant in the fuel elements usually exceeds 300 g s cm , but it requires a
large test facility to conduct burnout experiments on multi-rod bundles at
such values of mass flux. The large test rigs which have come into use in
more recent times are used mainly in the development of commercial designs of
reactor fuel elements and the results have been disclosed less often than
those of tests of a less specific nature performed with lower mass flux in
smaller rigs. The effect of the greater availability of data in the lower
ranges of mass flux is clearly seen in Figure 2; although there is a useful1 2
representation (10 per cent) of mass fluxes between 280 and 500 g s cm , a
substantial proportion (88 per cent) of the tests were performed with mass
fluxes less than 280 g s cm.
6.1.3 Inlet quality
Coolant qualities at channel inlet range from -1.08 to 0.895; Figure 3
shows the distribution of tests over this range. Negative quality is used to
indicate subcooled conditions and also to express the degree of subcooling.
Tests with the highest degree of inlet subcooling were performed at Bettis on
bundles of 20 triangularly pitched rods (assemblies 160, 162, 164 and 166) in
support of the LWBR program. The inlet pressure and temperature conditions
were 13.8 MPa, 93?C (2000 psia, 200?F). Tests with the highest quality of
mixture at inlet were performed at APED on a 2-rod assembly (assembly 145) in
support of the United States Atomic Energy Commission's Superheat Development
Program. Concentrations of tests are evident at frequently chosen inlet
conditions, particularly at qualities -0.64 (2000 psia, 400?F), -0.40 (2000
psia, 500?F), and -0.14 (which includes the 1200 psia, 500?F condition). The
-0.10 to -0.02 quality band which covers the design inlet conditions of most
boiling water reactors, contains 28 per cent of the tests included in the
compilation, and the -0.2 to -0.1 quality band contains 30 per cent. The
-0.40 to -0.30 quality band, which covers the most common design inlet
conditions of pressurised water reactors, contains 8 per cent of the tests.
Only 9 per cent of the tests were performed with positive quality inlet
conditions; Figure 3 shows very clearly the abrupt change in the distribution
of tests near the saturated inlet condition.
15
6.1.4 Quality at burnout
Coolant bulk qualities at burnout range from -0.484 to 0.999; Figure 4
shows the distribution of tests over this range. The burnout quality is
theoretical; it is the average quality of the coolant at the flow cross-
section which contains the burnout point and it is calculated from the inlet
condition of the coolant and the heat input up to the burnout section. When
the heat flux distribution is non-uniform, burnout may be detected at a number
of points simultaneously; in this case, the cross-section containing the
burnout point with the lowest local heat flux is regarded as the burnout
section. The quality depends, of course, upon the pressure at the relevant
cross-section, but only when burnout occurs at the channel exit can the
pressure at the burnout section be measured in a test. For this report,
burnout quality has been calculated at the system pressure which, in most (but
not all) cases, is the channel outlet pressure, regardless of the actual
position in the channel of the burnout section.
The tests which yielded the lowest burnout quality (or highest burnout
subcooling) were among those performed at Bettis on 20-rod bundles with the
lowest inlet quality; this burnout quality was closely approached, however,
in tests at SORIN on a 9-rod bundle (assembly 96) with higher inlet quality
and lower mass flux, but considerably smaller ratio of length to heated
equivalent diameter. The highest burnout qualities are not associated with
positive quality inlet conditions. All of the burnout qualities higher than
0.910 in the compiled data occur with sub-cooled inlet conditions and low mass
flux; the highest was reached in a CISE (Piacenza) program of tests on a very
long (6 m) 19-rod bundle (assembly 194).
The most frequent burnout qualities lie in a band between 0.20 and 0.31.
About 20 per cent of the tests are contained in this band, which is
approximately that in which burnout would occur in a boiling water reactor
core as a result of a rise in fission power or a reduction in coolant flow
rate.
6.1.5 Burnout heat flux
yLocal burnout heat fluxes range from 2.4 to 2220 W cm, but in only 0.5
per cent of the tests does the burnout heat flux exceed 1200 W cm"2. Figure 5
shows the distribution of tests over the significant part of the range. Here,
the term 'burnout heat flux' denotes the local value of the heat flux at the
16
point at which burnout was first detected. If it is inferred from the test
records that burnout occurred at a number of points simultaneously, the
compiled data enable the local heat flux at any of the detected initial
burnout points to be determined but, for the present purpose, the lowest value
is regarded as the burnout heat flux.
Both extremes of burnout heat flux occur in annular assemblies. The
lowest values come from tests at CRNL on short, internally heated annuli
(assemblies A18, A19) with a half-cosine, inlet peaked axial distribution of
heat flux and positive inlet quality. These very low burnout heat fluxes
occurred at the downstream end of an extensive burnout region. The lowest
heat flux at an isolated (or point) indication of burnout is 6.4 W cm" ; it
occurred at the outlet end of a long, uniformly-heated annulus (assembly A21)
tested at CISE (Piacenza) with positive inlet quality. The highest burnout
heat fluxes are associated with subcooled burnout at very high mass flux in
annular assemblies (assemblies A8 to A17) which were tested at SRL and
Columbia; all had downflow and some had heavy water coolant.
Burnout heat fluxes in non-annular assemblies are in the range 6.8 to 884
W cnT^. The lowest occurred in tests at CISE (Piacenza) on a 19-rod bundle of
length 6 m (assembly 194) with subcooled inlet conditions and low mass flux;
these were also the tests that yielded the highest burnout quality. The
highest burnout heat flux in a non-annular assembly occurred in tests at KEI
or, a single rod in a simulated concentric array (assembly 222). The highest
burnout heat flux in any of the multi-rod assemblies is 698 W cm" , which was
attained in further tests at KEI on a short 3-rod bundle (assembly 251).
Burnout heat flux was a dependent variable in the great majority of tests
(94 per cent); the histogram shows an asymmetrical distribution typical of a
random variable bounded at one extreme but not at the other. The effect of
constant heat flux tests (notably those performed on 3-rod and 7-rod bundles
at ABA) is, however, clearly discernible in concentrations of tests at9 2
100 W cm and, to a lesser degree, at other intervals of 25 W cm between 75?)
and 200 W cm . The most frequent burnout heat fluxes lie in the range 70 to
125 W cm , a band lower than that in which burnout would be expected in
water-cooled power reactor cores as a result of power increase or flow
reduction. This characteristic of the compiled data is largely due to the
abundance of tests with low mass flux which, with the same inlet condition,
tends to produce burnout at higher quality and lower heat flux. The influence
of the low mass flux data would have been more pronounced but for the opposing
17
influence of another characteristic, namely the presence of a large number of
tests performed on assemblies having a ratio of length to heated equivalent
diameter less thun that typical of power reactor fuel elements. This
characteristic will be discussed in Section 6.1.10.
6.1.6 Number of rods
Figure 6 shows that the number of rods represented varies from one to
thirty-seven, prominence being shared by the single rod of annular assemblies,
the nine rods of the most common square array, and the seven, nineteen and
thirty-seven rods of circular pitch arrays. It can be seen that single-rod
assemblies are not disproportionately represented and, therefore, that the
admission of tests performed on annular assemblies has been restricted to a
suitable level. Forty-five per cent of the tests included in the compilation
were performed on assemblies of 12 or more rods. The 37-rod assemblies and
some of the 19-rod assenblies are the only ones simulating entire reactor fuel
element assemblies. Many of the others represent regions of various extent in
reactor fuel elements, whereas some are special experimental arrangements used
in investigations of the effect of certain geometric characteristics on
burnout.
6.1.7 Rod diameter
The rod diameter in multi-rod bundles varies from 5 mm, found in some 3-
rod and 7-rod bundles, to 20 mm in the 19-rod bundles built to simulate the
fuel elements of natural uranium-fuel led reactors. Figure 7 shows the
distribution of tests over this range, but not the rod diameters of 25.4 and
54 mm found in a small number of tests on two annular assemblies. There has
been little attempt in burnout experiments to vary rod diameter systematically
and investigations have generally been confined to specific rod diameters used
in particular reactor designs. There is, however, enough variety in these to
provide a spread of diameters in the range 5 to 20 mm. The inclusion in the
compilation of a substantial amount of data made available to the authors by
the United Kingdom Atomic Energy Authority (UKAEA) is the cause of a prominent
concentration of tests at 16 mm (0.625 inch), the fuel rod diameter used in
the SGHWR. Other prominent concentrations occur at standard commercial tube
sizes and at 10.7 mm (0.422 inch) and 14.3 mm (0.5625 inch), the rod diameters
generally associated, respectively, with pressurised and boiling water
reactors.
18
6.1.8 Rod spacing
Rod spacing (expressed here as a ratio of rod pitch to rod diameter) is a
characteristic which, unlike rod diameter, has often been varied in
experiments to determine its effect on burnout. One such experiment,
conducted at KEI on a series of 3-rod bundles (assemblies 249 to 264),
provided data for the closest rod spacing with an average rod pitch/diameter
ratio of 1.01, the rods being nominally in contact along their entire length.
Data for the widest rod spacings, with rod pitch/diameter ratios ranging from
1.83 to 2.22, were provided by experiments conducted at ABA and ASEA on 6-,
7-, 9- and 37-rod bundles as part of the Marviken BHWR research program.
Figure 8 shows the distribution of tests over the range of rod spacing. A
large proportion of the tests were performed on assemblies with the rod
arrrangements of established reactor designs; the most frequent values of rod
pitch/diameter ratio are those associated with light water-moderated,
pressurised and boiling water reactors (1.31 to 1.33), the SGHWR (1.18 to
1.20), and the CIRENE heavy water-moderated, boiling water reactor (1.07 to
1.08).
6.1.9 Equivalent diameters and ratio of heated to wetted perimeter
Figure 9 shows the distribution of tests over the range of hydraulic
equivalent diameter and Figure 10 the distribution over the range of heated
equivalent diameter. Figure 11 shows the distribution over the range of the
ratio of the equivalent diameters which, more simply, is the ratio of heated
to wetted perimeters.
The range of hydraulic equivalent diameter extends from 2 mm occurring in
tests carried out at Columbia on a bundle of 12 wire-wrapped rods arranged on
a close triangular pitch in a close-fitting duct (assembly 7) to 39.5 mm in a
7-rod bundle (assembly 111) tested at ABA. Only 8 per cent of the tests were
performed on assemblies having a hydraulic equivalent diameter greater than
13.8 mm and virtually all of these were in support of BHWR programs> In these
experiments, a considerable variation of hydraulic equivalent diamc'? was
achieved by changing the dimensions of the ducts surrounding the rod bunuies.
Prominent concentrations of tests at 7.6 and 10.8 mm indicate the constancy of
hydraulic equivalent diameter maintained in tests supporting the CIRENE and
SGHWR programs respectively.
19
In the coolant flow channels of reactor fuel elements, the ratio of
heated to wetted perimeter is generally high, being about 0.8 in pressure tube
reactors and even higher in pressure vessel reactors. Burnout test assemblies
simulating entire fuel elements, such as the 37-rod and many of the 19-rod
bundles, naturally reproduce this ratio exactly, but assemblies of fewer rods
than the fuel element they represent cannot provide realistic ratios unless
the enclosing duct is heated. In a few test assemblies, the rods were
surrounded by heated rod segments which provided ratios of from 0.7 to 0.84,
but such complex test apparatus has usually been avoided and most of the
heated duct arrangements included in the compilation consist of three rods
surrounded by a fully-heated circular duct. The majority of the test
assemblies had unheated ducts and the range of heated to wetted perimeter
ratios found in the compilation extends to quite low values that are not
typical of reactor fuel elements. The lowest value (0.135) comes from tests
performed at MAN on a 4-rod assembly with only one rod heated (assembly 149).
The highest value in assemblies with some unheated surfaces is 0.834 and comes
from tests performed at ORNL on 7-rod bundles with heated surroundvng segments
(assemblies 184, 188 to 193). Thirty-two per cent of the tests in the
compilation are in the range 0.73 to 0.834, which might be considered typical
of reactor fuel elements. This range also contains the most frequent values
provided by tests on full simulations of the CIRENE and SGHWR pressure-tube
reactor fuel elements.
Heated equivalent diameter can be obtained by dividing the hydraulic
equivalent diameter by the ratio of heated to wetted perimeter. The
distribution of tests over the range of heated equivalent diameter shown in
Figure 10 is thus a modified form of the distribution shown in Figure 9. Fuel
elements of the Marviken heavy water reactor have a heated equivalent diameter
of 36.6 mm and values greater than this cannot be regarded as typical of
reactor fuel elements. The lowest and highest values in the compiled data are
2.75 and 85.4 mm; these belong to the assemblies with the smallest and
largest hydraulic equivalent diameters (assemblies 7 and 111). The CIRENE and
SGHUR programs of tests on full simulations of reactor fuel elements, being
highly consistent in both hydraulic equivalent diameter and heated to wetted
perimeter ratio, provided the most frequent values of heated equivalent
diameter at 9.7 and 13.5 mm.
20
6.1.10 Channel length, boiling length, and ratio of length to heated
equivalent diameter
Figure 14 shows the distribution of tests over the range of heated length
of rod, which extends from 100 mm for 1- and 3-rod assemblies tested at KEI
(assemblies 224, 258) to 8230 mm for a single, uninterrupted heater rod used
in a photographic study of transition boiling at APED (assembly 281). The
longest multi-rod assembly included in the compilation is a 6 m, 19-rod bundle
(assembly 194) tested at CISE (Piacenza) to provide information about the
effect of boiling length on burnout in reactor power channels. Various
channel lengths from 300 mm (11.5 inches) to 4600 mm (18 ft) are fairly evenly
represented but by far the most frequent lengths are 3658 mm (12 ft) and 1829
mm (6 ft), the former because it is the most common length for the active
region of power reactor fuel elements and the latter because many test rigs
have had insufficient power to produce burnout at typical reactor flow
conditions in multi-rod bundles of greater length.
More significant than channel length is the ratio of channel length to
heated equivalent diameter, a measure of overall similarity in assemblies of
different sizes. It is proportional to the ratio of heated surface area to
coolant flow area and, therefore, determines the relation between average heat
flux, coolant mass flux, and coolant enthalpy rise in channels of any size.
The distribution of tests over the range of this variable is shown in Figure
15. The range extends from 2.3 to 766.5, the least value occurring in a short
(100 mm) assembly with a single heated rod tested at KEI (assembly 224) and
the greatest in a 3.29 m long annular channel (assembly A21) tested at CISE
(Piacenza). The greatest ratio of length to heated equivalent diameter in a
multi-rod bundle is 721.0 which occurs in two bundles of 20 closely-spaced
rods, 2.39 m in length, used in tests at Bettis (assemblies 164, 166). In the
fuel elements of nuclear power reactors, the ratio of active length to heated
equivalent diameter usually exceeds 200, but two-thirds of the tests were
performed on assemblies in which this ratio was less than 200.
It is more appropriate, however, to look at boiling length, rather than
heated length, when considering the similarity of conditions at the burnout
section in assemblies of different sizes, because the ratio of boiling length
to heated equivalent diameter determines the relation between the average heat
flux in the boiling region, the coolant mass flux, and the coolant bulk
quality at the burnout section. Figure 16 shows the distribution of tests
over the range of boiling length and Figure 17 the distribution over the range
21
of the ratio of boiling length to heated equivalent diameter. Boiling length
is dependent on coolant conditions; it is considered here to have a value
only when the coolant is subcooled or saturated at the channel inlet and
burnout occurs in bulk boiling conditions. Valid boiling lengths can be
calculated for 78 per cent of the tests.
The range of boiling length extends from almost zero which occurs in many
assemblies to 6830 mm in the assembly with the greatest heated length
(assembly 281). The greatest boiling length in any of the multi-rod
assemblies is 5817 mm and occurs in the longest rod bundle (assembly 194).
The conspicuous concentration of tests in the narrow band of boiling length
250 to 300 mm is due to a large number of tests performed at ORNL on
assemblies 181, 184 and 188 to 193, which had boiling conditions over almost
their entire length of 295 mm. The ratio of boiling length to heated
equivalent diameter extends to 756.7 in the annular channels and 624.4 in the
multi-rod bundles. In this compilation the greatest ratios do not occur in
the channels with longest boiling length, but in those having the greatest
ratio of heated length to heated equivalent diameter (assemblies A21 and 166).
In 56 r cent of the tests which have a valid boiling length, the ratio of
boili ?ength to heated equivalent diameter is in the range 50 to 250; this
is roughly the range of the ratio at the burnout power level for normal flow
conditions in the fuel elements of water-cooled nuclear power reactors.
6.1.11 Distribution of heat flux
Only two characteristics of the heat flux distribution are considered
here; these are the transverse and axial form factors. The form factors are
defined as the ratio of the maximum to the mean heat flux, in the first case
over the heated perimeter of the flow channel and in the second, over the
heated length. Figures 12 and 13 show, respectively, the distributions of
tests over the ranges of the transverse and axial form factors in assemblies
with non-uniform distributions of heat flux.
In nearly all of the test assemblies providing data for this compilation,
any axial variation of the heat flux applies in a strictly similar manner to
all heated surfaces and therefore, in all tests on one assembly, both form
factors are constant. In the few cases in which the form factors vary (the
axial form factor from rod to rod and the transverse form factor from section
to section), mean values have been inserted in Table 2A and used in Figures 12
and 13. The mean transverse form factor is defined as that which would exist
22
if the duct and each rod were heated uniformly at their axially-averaged heai
flux; it is the ratio of the highest average heat flux on any rod (or duct)
to the average heat flux over the entire heated surface. The mean axial form
factor is defined as that which would exist if the heated perimeter at each
flow cross-section were heated uniformly at the transversely-averaged heat
flux and the peak heat fluxes on all rods were in the same cross-section;
thus, this factor is the ratio of the rod and duct peak heat fluxes averaged
over the heated perimeter to the average heat flux over the entire heated
surface. It should be noted that, whereas the product of constant transverse
and axial form factors is the channel peaking factor, the product of mean form
factors is meaningless.
The range of transverse form factor extends from values close to 1.0,
which occur mainly in assemblies with marginally different heat fluxes on the
rods and duct, to 3.36 in a test at KEI on a single-rod assembly (assembly
221), in which a part of the duct was heated at a low heat flux. Most of the
other large values of transverse form factor occurred in tests in which one or
more rods (or the duct) were heated at constant flux levels, while that on the
remaining rods was raised until burnout was detected. In this type of
experiment, the heat flux transverse form factor depends on the burnout heat
flux and varies from test to test on the same assembly. In such cases, Table
2A gives the average value of transverse form factor for all tests performed
on the assembly. The greatest systematic variation of heat flux across a rod
bundle, from 0.5 to 1.5 times the mean value, occurs in triangular pitch
arrays of 20 rods (assemblies 160, 162, 164, 265 to 268, 272, 273) which were
tested at Bettis as part of the LWBR development program. Data from tests on
full simulations of SGHWR fuel elements contribute to the high frequencies of
occurrence of the values 1.02 and 1.22.
In the great majority (99.4 per cent) of the tests with axi ally non-
uniform heating included in the compilation, the axial form factors range
between 1.16 and 1.86. These extreme values occur in assemblies having
asymmetric axial heat flux profiles with their peaks located in the downstream
half of the channel, the lower in a 9-rod bundle, 1.83 m in length (assembly
113) tested at ARC, the higher in a series of 16-rod bundles, 2.44 m in length
(assemblies 241 to 246), tested at Columbia. A small number of tests are
included in which the heat flux axial form factor exceeds 1.86, the greatest
value being 3.14. All of these large values occur in tests with heat flux
distributions containing 'spikes' or 'hot patches'. The most frequent form
factor in the non-uniform axial distributions of heat flux is 1.4; this is
23
often considered to be typical of the axial heat flux distribution in water-
cooled power reactors.
6.1.12 Boiling number, Weber number and Froude number
Non-dimensional compound variables can be useful indicators of similarity
in particular aspects of test conditions. Figures 18 to 20 show the
distributions of tests over the ranges of boiling number, Weber number and
Froude number.
Boiling number, which expresses the ratio of mass flux of vapour away
from the surface to the mass flux of fluid parallel to the surface, extends
-3 -3over the range 0.019 x 10 to 17.19 x 10 ; the lowest value occurs in a
3.29 m long annular channel (assembly A21) tested at CISE (Piacenza) and the
greatest in a 0.2 m long single-rod assembly simulating the central rod in a
circular pitch array (assembly 222) tested at KEI.
Weber number expresses the ratio of fluid inertial force to surface
tension force. When evaluated at the burnout cross-section, it extends over
the range 16.4 to 178 300; the lowest value occurs in a 7-rod bundle
(assembly 181) tested at low pressure and low mass flux at ORNL and the
highest in a 9-rod bundle (assembly 247) tested at high pressure and high mass
flux at Columbia.
Froude number expresses the ratio of fluid inertial force to
gravitational force. A factor which has sometimes been found useful in
correlating burnout data is the liquid Froude number which, in the compiled
data, extends over the range 0.004 to 3036; the lowest value occurs in the 7-
rod bundle (assembly 181) tested at low mass flux and the highest in a 12-rod
bundle with a very small equivalent diameter (assembly 7) tested at fairly
high mass flux at Columbia.
6.2 Distribution of Tests Over the Ranges of Two or More Variables Considered
Simultaneously
The histograms that have been described in Section 6.1 have shown how the
tests included in the compilation are distributed over the ranges of single
variables; each variable was considered separately and without regard for the
concurrent values of other variables. The term 'single variable' includes
simple variables, like pressure and mass flux, and compound variables (which
24
are fixed combinations of simple variables) like the non-dimensional groups.
However, to assess the relevance of the test data to any nominated set of
conditions, it is essential to know how different variables are associated by
value in the data; in this section, two or more variables, either simple or
compound, are considered simultaneously and independently. The full range of
each variable is divided into a number of intervals and the test condition
field is thereby divided into regions, each region being defined by a
different combination of intervals of the variables. In the case of two
variables, the distribution of tests can be displayed as a simple table of the
number of tests occurring in each region, the columns corresponding to
intervals of one variable and the rows to intervals of the other. Tables 7 to
26 are displays of this kind. When four variables are considered, the display
becomes a two-dimensional array, the elements of which are also two-
dimensional arrays. The columns and rows of the main array correspond to
intervals of two of the variables and the columns and rows of each inner array
to intervals of the other two variables. Tables 27 to 31 are displays of this
kind.
Tables 7 to 17 each show a distribution of tests among regions defined by
a different pair of variables. The range of each variable has been divided
into equal intervals. This method of dividing the ranges superimposes the
separate distributions of the variables and, since these are very irregular in
most cases, it produces many regions containing small numbers of tests (or
none at all) and some containing large numbers of tests. When the purpose is
to reveal the disposition of data in the compilation, regions containing no
tests are as significant as those containing many and equal division of the
variable ranges is preferable. Tables 7 to 17 show clearly the regions in
which data are concentrated and those in which they are sparse. They also
reveal many special characteristics of the data distribution: for example,
the limited pressure range of tests with very high mass flux or very high
local burnout heat flux (Tables 7,8) and the differing mass flux and burnout
heat flux ranges associated with subcooled and quality burnout (Tables 10,17).
When, however, the purpose is to show how the distribution of tests over
the range of one variable changes with the value of another, all intervals
should have the same weight and therefore should contain the same number of
tests. Tables 18 to 26 each show a distribution of tests among regions
defined by a different pair of variables, the range of each variable being
divided as nearly as possible into intervals containing equal numbers of
25
tests. This method of dividing the ranges suppresses display of the separate
distributions of each variable and allows the relative distribution to be
seen. The same number of tests in every region would not necessarily indicate
a uniform distribution of tests over the range of each variable, but rather a
uniform association of the variables throughout the tests. Variations in the
numbers of tests from region to region indicate a changing association of the
variables; for instance, Table 18 indicates that although very low pressures
are mainly associated with either very low or very high mass fluxes, medium
pressures are mainly associated with medium mass fluxes and high pressures
with high (but not low) mass fluxes.
When four variables are considered simultaneously, division of their
ranges into many intervals produces a distribution table that is
inconveniently large. From five to eight intervals, as used in Tables 27 to
31, is a practical choice. As the number of intervals is reduced, the empty
columns or rows that are characteristic of equal range intervals become less
tolerable; therefore, in all of the tables for four variables given here,
intervals containing similar numbers of tests have been chosen. Tables 27 to
29 show distributions of tests among regions defined by intervals of heated
equivalent diameter, pressure, mass flux, and one other variable, which may be
inlet quality, bulk quality at burnout, or average surface heat flux at
burnout. Table 30 shows the distribution in relation to four non-dimensional
variables, namely the boiling, Weber and Froude numbers, and the bulk quality
at burnout. A distribution of tests in relation to four geometric variables
(number of rods, rod diameter, ratio of rod pitch to diameter, and ratio of
length to heated equivalent diameter) is shown in Table 31.
7. GENERAL DISCUSSION
It has been pointed out (in Sections 1 and 6.1.6) that the results of
burnout experiments on large rod bundle assemblies are seldom published,
because they might reveal proprietary information about commercial design of
fuel elements. On the other hand, the results of investigations carried out
with smaller assemblies into more general aspects of burnout are very often
published. It is therefore a feature of data compilations derived from
published information that they contain a significant amount of data relating
to small-scale experiments which do not reproduce simultaneously all of the
characteristics and operating conditions of a reactor fuel element. In the
compilation described here, this situation is partly relieved by the inclusion
26
of confidential data made available to the authors by the UKAEA.
Nevertheless, a large part of the data derives from small-scale experiments
with bundles of nine rods or less. One effect of the small-scale test
component is that although the ranges of important variables encompass typical
reactor conditions, distributions of the tests over the ranges are often not
centred upon these typical conditions. Particular examples of this are the
distributions with respect to mass flux, burnout heat flux, and ratio of
heated length to heated equivalent diameter, all of which have been discussed
(see Sections 6.1.2, 6.1.5 and 6.1.10).
The inherent characteristics of the BACE compilation as a single body of
data are not of great importance, however, because it should be regarded, not
as an indivisible body, but as a pool from which suitable data may be selected
for particular purposes. A substantial amount of data is included for larger
scale tests on bundles of from 16 to 37 rods at conditions close to those of
normal reactor operation. Small-scale tests, however, contribute most of the
data for burnout at high mass flux, high heat flux, high inlet quality, and
close rod spacing.
The ranges of the principal variables are extensive and, considered
separately, embrace most of the conditions likely to occur in the normal
operating and possible emergency states of water-cooled nuclear power
reactors. Considered simultaneously, the ranges of the many variables define
a vast field of conditions which is not fully represented in the compilation;
areas in the vicinity of reactor operating conditions are well populated with
tests, but fringe areas are thinly and irregularly populated. Generally,
tests which extend the range of a variable beyond the limits of normal reactor
operation do so within very narrow bands of other variables. This means that
if burnout data for extreme values of a variable are sought from the
compilation, there is little choice of the concurrent values of other
variables.
8. CONCLUSIONS
(a) The distributions of burnout tests over the ranges of important
variables considered singly, or simultaneously in pairs or sets of four, are
presented in sufficient detail as histograms and tables to enable a
prospective user to determine the relevance of the data to any conditions of
particular interest.
27
(b) The distribution tables, especially those for four variables,
indicate very clearly the dispersion of data due to the number of variables
involved and the small ness of the sample that can result from the placing of
close limits on more than one variable. The adequacy of the present
compilation to provide significant samples of data varies considerably with
the location and delimitation of the area of interest. If, however, the
number and range of governing variables are chosen with discretion, the
compilation provides an effective data base for operations such as:
(i) surveys of parametric effects on burnout conditions,
(ii) tests of the accuracy of burnout prediction formulas, and
(iii) optimisation of the empirical coefficients in burnout
formulas.
(c) The possible ranges of the many important variables define a vast
condition field; it is evident from the sparse and irregular distribution of
burnout tests over the greater part of this field that the present
compilation, despite the number of tests, is not completely adequate and that
its usefulness can be increased by the addition of more data, especially in
the fringe areas of the condition field.
9. ACKNOWLEDGEMENTS
The authors gratefully acknowledge the valued assistance of Mr N.D.
Hargreaves and Mr D. Paton, who shared in the onerous tasks of collecting and
processing the data, and the helpful advice and encouragement of Dr K.R.
Lawther, under whose general direction the work was carried out.
28
10. REFERENCES
10.1 General
Barnett, P.G. [1966] - A correlation of burnout data for uniformly heated
annuli and its use for predicting burnout in uniformly heated rod
bundles. AEEW-R463.
Barnett, P.G. [19683 - A comparison of the accuracy of some correlations for
burnout in annuli and rod bundles. AEEW-R558.
Hughes, E.D. [1970a] - An examination of rod bundle critical heat flux data
and correlations and their applicability to loss-of-coolant accident
analyses. IN-1319.
Hughes, E.D. [1970b] - A correlation of rod bundle critical heat flux for
water in the pressure range 150 to 725 psia. IN-1412.
Hughes, E.D., Ka-Lam Ip , Baker, A.N. and Carbon, M.W. [1974] - A compilation
of rod array critical heat flux data sources and information. Nucl.
Eng. Des., 30:20-35.
Lintner, M.A. [1970] - ERREST, a program to edit data, perform error
calculations, and do nonlinear least square parameter estimations.
Idaho Nuclear Corp. report, distributed by the Argonne Code Center.
Macbeth, R.V. [1964] - Burnout analysis Part 5: examination of published
world data for rod bundles. AEEW-R358*
Mironov, Yu. V., Razina, N.S., Smolin, V.N. and Shpanskii, S.V. [1978] - Pool
of experimental data on critical heat flux with water boiling in rod
assemblies. Teploenergetika, 25(9)65-67.
long, US., Currin, H.B. and Engel, F.C. [1964] - DNB (burnout) studies in an
open lattice core. Vol. II, WCAP-3736.
long, L.S. [1969] - Critical heat fluxes in rod bundles. Proc. ASME Symp. on
Two-Phase Flow and Heat Transfer in Red Bundles, Los Angeles,
November, pp.31-46.
29
Tong, L.S. [1972] - Boiling crisis and critical heat flux. TID-25887.
10.2 Sources of Published Data
[1] Janssen, E. and Kervinen, J.A. [1963] - Burnout conditions for
single rod in annular geometry, water at 600 to 1400 psia. GEAP-
3899.
[2] Hench, J.E. [1963] - Multirod (four-rod) critical heat flux at 1000
psia. GEAP-4358.
[3] Matzner, B. [1961] - Basic experimental studies on boiling fluid
flow and hc-dt transfer at elevated pressures. Monthly Progress
Report for November 1961. TID-14439.
[4] Matzner, B. [1963] - Basic experimental studies of boiling fluid
flow and heat transfer at elevated pressures. Monthly Progress
Report for February 1963. TID-18296.
[5] Matzner, B. [1961] - Basic experimental studies on boiling fluid
flow and heat transfer at elevated pressures. Monthly Progress
Report for May 1961. TID-12574.
[6] Matzner, B. [1961] - Basic experimental studies on boiling fluid
flow and heat transfer at elevated pressures. Monthly Progress
Report for July 1961. TID-13711.
[7] Matzner, B. [1963] - Heat transfer and hydraulic studies for SNAP-4
fuel element geometries. Topical Report No.2. TID-19563.
[8] Macbeth, R.V. [1964] - Burnout analysis Part 5: examination of
published world data for rod bundles. AEEW-R358.
[9] Edwards, P.A. [1976] - An experimental study of burnout and pressure
drop in 19-rod clusters. AEEW-R371. (Reprint).
[10] Excluded from this report.
[11] Janssen, E. [1968] - Nine-rod critical heat flux investigation,
steam-water at 600 to 1400 psia. Final Summary Report. GEAP-5616.
30
[12] Becker, K.M., Hernborg, G., Bode, M. and Eriksson, 0. [1965] -
Burnout data for flow of boiling water in vertical round ducts,
annuli and rod clusters. AE-177.
[13] Becker, K.M. [1967] - A burnout correlation for flow of boiling
water in vertical rod bundles. AE-276.
[14] Nylund, 0., Becker, K.M., Eklund, R., Gelius, 0., Haga, I., Hansson>
P.T., Hernborg, G. and Akerhielm, F. [1967] - Measurements of
hydrodynamic characteristics, instability thresholds, and burnout
limits for 6-rod clusters in natural and forced convection. ASEA
and AB Atomenergi Report FRIGG-1.
[15] Nylund, 0., Becker, K.M., Eklund, R., Gelius, 0., Hernborg, G.,
Rouhani, Z. and Akerhielm, F. [1968] - Hydrodynamic and heat
transfer measurements on a full-scale simulated 36-rod Marviken fuel
element with uniform heat flux distribution. ASEA and AB Atomenergi
Report FRIGG-2.
[16] Becker, K.M. [1967] - Measurements and predictions of burnout
conditions in rod bundles. AES-366.
[17] Matzner, B. and Casterline, J.E. [1965] - The effect of length and
pressure on the critical heat flux for a closely spaced 19-rod
bundle in forced convection boiling. TID-22539.
[18] Hesson, G.M., Fitzsimmons, D.E. and Batch, J.M. [1965]
Experimental boiling burnout heat fluxes with an electrically heated
19-rod bundle test section. BNWL-206.
[19] Kunsemiller, D.F. [1966] - Multirod, forced flow, transition and
film boiling measurements. GEAP-5073.
[20] Adorni, N., Gaspari, G.P., Germani, G., Peterlongo, G., Ravetta, R.
and Zavattarelli, R. [1964] - Heat transfer crisis with steam-water
mixtures in complex geometries. CISE R-123.
[21] Adorni, N., Gaspari, G.P., Germani, F., Hassid, A., Ravetta, R. and
Rubiera, L. [1966] - Heat transfer crisis and pressure drop with
steam-water mixtures: Experimental data with seven rod bundles at
31
50 and 70 kg/cm2. CISE R-170.
[22] Excluded from this report.
[23] Excluded from this report.
[24] Excluded from this report.
[25] Campanile, A., Galimi, G. and Goffi, M. [1966] - Forced convection
burnout and hydrodynamic instability experiments for water at high
pressure. Part II. EUR-2963e.
[26] Excluded from this report.
[27] Polomik, E.E. and Quinn, E.P. [1962] - Multi-rod burnout at high
pressure. GEAP-3940.
[28] Matzner, 3. [1962] - Basic experimental studies on boiling fluid
flow and heat transfer at elevated pressures. Monthly Progress
Report for April 1962. TID-15637.
[29] Nylund, 0., Becker, K.M., Eklund, R., Gelius, 0., Haga, I., Jensen,
A., Malnes, D., Olsen, A., Rouhani, Z., Skaug, J. and Akerhielm, F.
[1969] - Hydrodynamic and heat transfer measurements on a full-scale
simulated 36-rod Marviken fuel element with non-uniform radial heat
flux distribution. ASEA-ATOM Report FRIGG-3.
[30] Nylund, 0., Becker, K.M., Eklund, R., Gelius, 0., Jensen, A.,
Malnes, D., Olsen, A., Rouhani, Z. and Akerhielm, F. [1970] -
Hydrodynamic and heat transfer measurements on a full scale
simulated 36-rod BHWR fuel element with non-uniform axial and radial
heat flux distribution. ASEA-ATOM Report FRIGG-4.
[31] Campanile, A., Galimi, G., Goffi, M. and Passavanti, G. [1970] -
Forced convection burnout and hydrodynamic instability experiments
for water at high pressure. Part VI. EUR-4468e.
[32] Campanile, A., Galimi, G. and Goffi, M. [1968] - Forced convection
burnout and hydrodynamic instability experiments for water at high
pressure. Part IV. EUR-3881e.
32
[33] Campanile, A., Gallmi, G., Goffi, M. and Passavanti, G. [1970] -
Forced convection burnout and hydrodynamic instability experiments
for water at high pressure. Part VII. EUR-4514e.
[34] Wilson, R.H., Stanek, L.J., Gellerstedt, J.S. and Lee, R.A. [1969]
- Critical heat flux in a non-uniformly heated rod bundle. Proc.
ASME Symp. on Two-Phase Flow and Heat Transfer in Rod Bundles, Los
Angeles, November, pp.56-62.
[35] Gellerstedt, J.S., Lee, R.A., Oberjohn, W.J., Wilson, R.H., and
Stanek, L.J. [1969] - Correlation of critical heat flux in a bundle
cooled by pressurised water. Proc. ASME Symp. on Two-Phase Flow and
Heat Transfer in Rod Bundles, Los Angeles, November, pp.63-71.
[36] Janssen, E., Schraub, F.A., Nixon, R.B., Matzner, B., and
Casterline, J.E. [1969] - Sixteen-rod heat flux investigation,
steam-water at 600 to 1250 psia. Proc. ASME Symp. on Two-Phase Flow
and Heat Transfer in Rod Bundles, Los Angeles, November, pp.81-88.
[37] Cermak, J.O., Farman, R.F., Tong, L.S., Casterline, J.E., Kokolis,
S. and Matzner, B. [1969] - The departure from nucleate boiling in
rod bundles during pressure blowdown. J. Heat Transfer (Trans.
ASME), 92C(4)621-627.
[38] Israel, S., Casterline, J.E. and Matzner, B. [1969] - Critical heat
flux measurements in a 16-rod simulation of a BWR fuel assembly. J.
Heat Transfer (Trans. ASME), 91C(3)355-363.
[39] Janssen, E. [1971] - Two-phase flow and heat transfer in multirod
geometries. Final Report. GEAP-10347.
[40] Waters E.D., Hesson, G.M., Fitzsimmons, D.E. and Batch, J.M. [1963]
- Boiling burnout experiments with 19-rod bundles in axial flow.
HW-77303.
[41] LeTourneau, B.W. and Green, S.J. [1971] - Critical heat flux and
pressure drop tests with parallel upflow of high pressure water in
bundles of twenty 1/2-in. rods. Nucl. Sci. Eng. 43(1)90-104.
33
[42] Hesson, G.M., Fitzsimmons, D.E. and Batch, J.M. [1964] - Boiling
burnout experiments with fog-cooled nineteen-rod bundle test
sections. HW-80523-REV1
[43] Hesson, G.M., Fitzsimmons, D.E. and Batch, J.M. [1964] - Comparison
of boiling burnout data for 19-rod bundles in horizontal and
vertical positions. HW-83443-REV1.
[44] Batch, J.M. and Hesson, G.M. [1964] - Comparison of boiling burnout
data for 19-rod bundle fuel elements spaced with 'wires' and
'warts'. HW-80391-REV1.
[45] Lahey, R.T., Kong, Y.H., Radcliffe, D.W. and Kiernan, S.A. [1972] -
Deficient cooling. Tenth Quarterly Progress Report. GEAP-10221-10.
[46] Kervinen, J.A., Kong, Y.H., Radcliffe, D.W. and Clay, D.G. [1972] -
Deficient cooling. 12th Quarterly Progress Report. GEAP-10221-12.
[47] Towel 1, R.H. [1965] - Effect of spacing on heat transfer burnout in
rod bundles. DP-1013.
[48] Hench, J.E. [1964] - Transition and film boiling data at 600, 1000
and 1400 psia in forced convection heat transfer to water. GEAP-
4492.
[49] Kastner, W. and Mayinger, F. [1970] - Burnout tests in connection
with safety research. Final Report. Parts I and II. AEC-tr-7394.
[50] Bowring, R.W. and Spigt, C.L. [1965] - Seven-rod bundle, natural -
circulation, stability and burnout tests with water at up to 28
atmospheres pressure. Nucl. Sci. Eng., 22(1)1-13.
[51] Becker, K.M., Flinta, J., Hernborg, G., Nylund, A., Nilsson, L. and
Jensen, A. [1968] - Experimental studies of burnout conditions in
vertical channels. AES-387.
[52] LeTourneau, B.W., Gavin, M.E. and Green, S.J. [1974] ~ Critical heat
flux and pressure drop tests with parallel upflow of high pressure
water in bundles of twenty 3/4-in. rods. Nucl. Sci. ,Eng.,
54(2)214-242.
34
[53] Smolin, V.N. and Polyakov, V.K. [1967] - Critical heat flux with
longitudinal flow round a rod bundle. Teploenergetika, 14(4)54-58.
[54] Gaspari, 6.P., Hassid, A., Ravetta, R. and Rubiera, L. [1968] - Heat
transfer crisis and pressure drop with steam-water mixtures in a
nineteen uniformly heated rod bundle. CISE R-264.
[55] Gaspari, G.P., Ravetta, R., Rubiera, L. and Vanoli, G. [1970] - Heat
transfer crisis and pressure drop measurements with steam-water
mixtures in nineteen rod clusters. CISE R-294.
[56] long, L.S., Chelemer, H., Casterline, J.E. and Matzner, B. [1967] -
Critical heat flux (DNB) in square and triangular array rod bundles.
Proc. JSME 1967 Semi-International Symp., Tokyo, September, pp.25-
34.
[57] Evangelisti, R., Gaspari, G.P., Rubiera, L. and Vanoli, G. [1972] -
Heat transfer crisis data with steam-water mixture in a sixteen-rod
bundle. Int. J. Heat Mass Transfer, 15:387-402.
[58] Nylund, 0. [1969] - Full-scale loop studies of BHWR and BWR fuel
assemblies. ASEA (Allm. Sven. Elektr. A.B.) Res., 10:63-125.
[59] Weisman, J., Wenzel, A.H., Tong, 1.3., Fitzsimmons, D.E., Thorne, W.
and Batch, J.M. [1968] - Experimental determination of the departure
from nucleate boiling in large rod bundles at high pressures. Chem.
Eng. Prog. Symp. Series, 64(82)114-125.
[60] Jones J.K. [1969] - An experimental study of the critical heat flux
for low pressure boiling water in forced convection in a vertical
seven heater rod bundle. ORNL-TM-2122.
[61] Gaspari, G.P., Hassid, A., Ravetta, R. and Rubiera, L. [1968] - Heat
transfer crisis and pressure drop with steam-water mixtures: Further
experimental data with seven-rod bundles. CISE R-208.
[62] Gaspari, G.P., Ravetta, R., Rubiera, L. and Vanoli, G. [1973] - Heat
transfer crisis and pressure drop measurements with steam-water
mixture in CIRENE 19-rod clusters (4 m long). CISE R-339.
35
[63] Ceresa, I., Gaspari, G.P., Lucchini, F. and Rubiera, L. [1973] -
Heat transfer crisis and pressure drop measurements with steam-water
mixtures in a 6-metre-long 19-rod cluster. CISE R-340.
[64] Excluded from this report.
[65] Marinelli, V., Gaspari, G.P., Greco, G. and Lucchini, F. [1975] -
Dryout experiments in a 16-rod BWR geometry with six different
radial heat flux distributions. ASME 75-HT-24.
[66] Moeck, E.O., Garg, S.C., Wikhammer, G.A., Stern, F. and Dempster,
R.T. [1966] - 'SWIFT' dryout data for a 19-rod, 3.25 inch diameter
bundle cooled by steam-water fog at 515 psia. AECL-2586.
[67] Marinkovitch, P.S. and Coeling, K.J. [1976] - Critical heat flux and
pressure drop tests with high pressure water in a bundle of 0.571
and 0.526 in. dia. rods with a non-uniform radial and axial heat
flux distribution. WAPD-TM-1162.
[68] Peterson, A.C. and Green, S.J. [1975] - Critical heat flux and
pressure drop tests with parallel upflow of high pressure water in
bundles of twenty-nine 0.301 in. dia. rods with a non-uniform radial
and axial heat flux distribution. WAPD-TM-1170.
[69] Yates, 0., Galbraith, K. and Collingham, R. [1975] - DNB and post
DNB heat transfer data in 25-rod bundles. XN-75-54.
[70] Green, S.J., Maurer, G.W. and Weiss, A. [1962] - Burnout and
pressure-drop studies for forced-convection flow of water parallel
to rod bundles. ASME 62-HT-43.
[71] Bezrukov, Yu. A., Astakhov, V.I., Brantov, V.G., Abramov, V.I.,
Testov, I.I., Logvinov, S.A. and Rassokhin, N.G. [1976] -
Experimental investigation and statistical analysis of data on
burnout in rod bundles for water-moderated water-cooled reactors.
Teploenergetika, 23(2)80-82.
[72] Yefimov, V.A., Marchenko, L.D. and Trutnev, D.P. [1969] - Study of
the effect of rod bundles on boiling crisis. Heat Transfer-Sov.
Res., 1(4)42-47.
36
[73] Yamazaki, Y., Iguchi, T., Niitsuma, Y. and Takano, K. [1975a] -
Effect of the heated length on the burnout heat flux in the rod
bundle test section. JAERI M-6030.
[74] Yamazaki, Y., Iguchi, T., Niitsuma, Y. [1975b] - Burnout heat flux
of narrow spaced rod bundles. Effect of flow rate and steam
quality. JAERI M-6031.
[75] Kunsemiller, D.F. [1965] - Transition boiling heat transfer program.
Twelfth Quarterly Progress Report: (Task A-2 multirod tests).
GEAP-5081.
[76] Rosal, E.R., Cermak, J.O., Tong, L.S., Casterline, J.E., Kokolis, S.
and Matzner, B. [1974] - High pressure rod bundle DNB data with
axially non-uniform heat flux. Nucl. Eng. Des., 31:1-20.
[77] Yefimov, V.A., Trutnev, D.P. and Marchenko, L.D. [1969] - " ;tudy of
the boiling crisis with water in rod bundles. Heat Transfer-Sov.
Res., 1(4)48-56.
[78] LeTourneau, B.W., Peterson, A.C., Coeling, K.J., Gavin, M.E. and
Green, S.J. [1975] - Critical heat flux and pressure drop tests with
parallel upflow of high pressure water in bundles of twenty 0.25 and
0.28 inch diameter rods. WAPD-TM-1013.
[79] Quinn, E.P. and Swan, C.L. [1964] - Visual observations of fluid
behaviour in high-pressure transition boiling flows. GEAP-4636.
[80] Swan, C.L. [1966] - Photography of heated surface fluid behaviour
for transition boiling at 1000 psia. GEAP-5094.
[81] Lund, K.O. [1975] - Critical heat flux in a subcooled, low-pressure
rod-bundle with various rod spacings. ASME 75-HT-49.
[82] Green, S.J., LeTourneau, B.W. and Peterson, A.C. [1970] - Thermal
and hydraulic effects of crud deposited on electrically heated rod
bundles. WAPD-TM-918.
[83] Larsen, P.S., Kitzes, A.S., Stormer, T.D., Green, J. and Tong, L.S.
[1966] - DNB measurements for upwards flow of water in an unheated
37
square channel with a single uniformly heated rod at 1600-2300 psia.
Proc. ASME 3rd International Heat Transf. Conf., Chicago.
[84] Little, R.B. [1970] - Dryout tests on an internally heated annulus
with variation of axial heat flux distribution. AEEW-R578.
[85] Janssen, E. and Kervinen,J.A. [1963] - Burnout conditions for non-
uniformly heated rod in annular geometry, water at 1000 psia.
GEAP-3755.
[86] Knoebel, D.H., Harris, S.D., Grain, B. Jr. and Biderman, R.M.
[1973] - Forced-convection subcooled critical heat flux. DP-1306.
[87] Abraham, S.C., Macdonald, I.P.L., Moeck, E.O. and Wikhammer, G.A.
[1966] - The effect of cosine and half-cosine heat fluxes on dryout
for steam-water flow in an annulus at 1000 psia. AECL-2646.
[88] Quinn, E.P. [1965] - Single-rod, forced flow, transition boiling
heat transfer from smooth and finned surfaces. GEAP-4786.
[89] Era, A., Gaspari, G.P., Hassid, A., Milani, A. and Zavattarelli, R.
[1966] - Heat transfer data in the liquid deficient region for
steam-water mixtures at 70 kg/cm flowing in tubular and annular
conduits. CISE R-184.
[90] Judd, D.F., Wilson, R.H., Welch, C.P. and Lee, R.A. [1967] - Non-
uniform heat generation experimental program. Final Report. BAW-
3238-13.
[91] long, L.S., Currin, H.B. and Engel, F.C. [1964] - DNB (burnout)
studies in an open lattice core. Vol. 1. WCAP-3736.
38
11. NOTATION
Symbols
A channel flow area
Bo boiling number
D hydraulic equivalent diameter
D^ heated equivalent diameter
Fr Froude number (liquid)
G coolant mass flux
g acceleration due to gravity
h coolant enthalpy
L heated length of channel
P^ heated perimeter of flow channel
P.. wetted perimeter of flow channelW
q heat flux
We Weber number
X coolant quality
p coolant density
a surface tension
39
Subscripts
a
b
c
e
f
fg
9
h '
average
bulk
critical, i.e. at
hydraulic equival
of the saturated
of vaporisation
burnout
ent
liquid
of the dry, saturated vapour
heated
m of the two-phase mixture
w wetted
.v.iTibolic Names of Variables Used in Tables
BO boiling number
G coolant mass flux
HEQD heated equivalent diameter
L/D ratio of heated length to heated equivalent
di ameter
LFR liquid Froude number
P system pressure
QBAV average heat flux at the burnout section
QBO local burnout heat flux
RDIA rod diameter
40
RODS number of rods
WE Weber number
XBO coolant bulk quality at the burnout section
XIN coolant bulk quality at the channel inlet
12. GLOSSARY
Some of the terms used have well-established meanings, others have not.
The definitions given here pertain strictly to the use of the terms in this
report and are not necessarily applicable to the terms as they may be used
generally in the literature.
Boiling length
The length of channel between the flow cross-section, at which the bulk
enthalpy of the coolant is that of the saturated liquid, and the burnout
cross-section.
Boiling number
A non-dimensional compound variable defined by the equation:
H/NJJ
Bulk
When applied to a condition of the coolant, this indicates the average,
condition over a flow cross-section calculated assuming thermal equilibrium
(as in bulk enthalpy, bulk quality).
Bulk boiling
A condition of the coolant in which its bulk enthalpy lies between the
enthalpies of the saturated liquid and the dry, saturated vapour at the
prevailing pressure.
41
Burnout
One of the following:
(a) A sudden and disproportionate increase in the temperature of a
heated surface, resulting from a very small increase In the surface
heat flux or a very small change in the condition of the coolant.
(b) The onset of a marked increase in the rate at which the temperature
of a heated surface rises with increase 6f surface heat flux or with
change in a particular condition of the coolant.
Burnout condition
The critical combination of coolant bulk conditions and surface heat flux
at which burnout occurs. A local burnout condition is defined by the local
heat flux, and an average burnout condition by the average heat flux over the
heated perimeter of the burnout section.
Burnout heat flux
The surface heat flux at which burnout occurs. A local burnout heat flux
is the value of the heat flux at the burnout point. An average burnout heat
flux is the average surface heat flux over the heated perimeter of the flow
cross-section containing a burnout point.
Burnout point
A point on a heated surface where burnout first occurs.
Burnout power
The heating power input to a heated channel at the onset of burnout.
Burnout quality
The bulk quality of the coolant at a burnout section.
Burnout section
A flow cross-section containing a burnout point.
42
Burnout subcooling
The subcooling of the coolant at a burnout section.
Channel peaking factor
The ratio of the maximum local heat flux occurring in a channel to the
average heat flux over the entire heated surface.
Circular pitch
Describes a rod array in which the rod centres are evenly spaced around
the circumferences of concentric circles. One rod may be placed at the common
centre.
Compound variable
An association of two or more independent variables in a fixed relation.
Critical heat flux
Synonymous with 'burnout heat flux1
Departure from nucleate boiling (DNB)
A sudden transition from heat transfer by bubble nucleation at a heated
surface to heat transfer through a vapour film, causing burnout, usually of
category (a).
Dryout
A transition from heat transfer through a thin liquid film to heat
transfer through a vapour, causing burnout, often of category (b).
Flow cross-section
A cross-section of the flow passage normal to the principal direction of
flow.
Form factor
The ratio of the maximum local value of a variable, which varies
spatially over an axis or plane, to the average value over the axis or plane.
Hence, an axial form factor is a form factor with reference to the
43
longitudinal axis of a rod or channel, and a transverse form factor is one
with reference to a cross-section of a channel.
Froude number
A non-dimensional compound variable defined by the equation:
r2Fr = G
'f 9De
Heated equivalent diameter
A variable defined by the equation:
Hydraulic equivalent diameter
A variable defined by the equation:
Percentile division
Division of the range of a variable into intervals having approximately
equal numbers of tests. Thus, in ten divisions, each interval contains ten
per cent of the total number of tests and in five divisions each contains
twenty per cent.
Quality
In two-phase flows, the ratio of the mass flow rate of vapour to the
total mass flow rate at a flow cross-section. When the bulk enthalpy is below
that of the saturated liquid, it is a notional quantity defined by the
equation:
h-hf
Y - _ L" ^
Subcooled
Having a bulk enthalpy less than that of the saturated liquid at the
prevailing pressure.
44
Subcooling
Generally, the difference between the enthalpy of the saturated liquid
and the bulk enthalpy of the coolant. In this report, it is the ratio of this
difference to the latent heat of vaporisation, numerically equal but opposite
in sign to quality in a subcooled fluid.
Surface boiling
Local boiling at a heated surface when the coolant is sub-cooled.
System pressure
The pressure at the outlet of the- heated channel, where it is included in
or can be derived from the recorded data; otherwise, it is the pressure at
the inlet of the heated channel.
Weber number
A non-dimensional compound variable defined by the equation:
,2
We DeGm
13. ABBREVIATIONS USED IN THE TEXT
13.1 Laboratory Names and Locations and Number of Tests
Abbreviation
ABA
AEEW
ANL
APED
ARC
ASEA
Bettis
Full Name and Location
Heat Engineering Laboratory, Aktiebolaget
Atomenergi, Studsvik, Sweden.
United Kingdom Atomic Energy Authority, Atomic
Energy Establishment, Winfrith.
Argonne National Laboratory, Argonne, Illinois.
Heat Transfer Facility, Atomic Power Equipment
Department, General Electric Co., San Jose, -Calif.
Alliance Research Centre, Babcock and Mil cox Co.,Alliance, Ohio.
ASEA-ATOM (Allmanna Svenska Elektriska Aktiebolaget),
Vasteras, Sweden.
Bettis Atomic Power Laboratory, Westinghouse Electric
Corp., West Mifflin, Pennsylvania.
Number
of tests
792
2260
60
1100
642
286
925
45
CISE Centro Informazioni Studi Esperienze, Heat Transfer 466
(Genoa) Facility, Stabi1imento Meccanico Ansaldo, Genoa, Italy.
CISE Centro Informazioni Studi Esperienze, Heat Transfer 1677
(Piacenza) Facility, Ente Nazionale per 1'Energia Elettrica,
Emilia Power Station, Piacenza, Italy.
Columbia Heat Transfer Research Facility, Department of 1323
Chemical Engineering, Columbia University, New York.
CRNL Chalk River Nuclear Laboratories, Atomic 95
Energy of Canada Ltd, Ontario, Canada.
CMC Atomic Energy Department, Canadian Westinghouse 75
Co., Hamilton, Ontario, Canada.
ETU Eindhoven Technological University, Eindhoven, 7
The Netherlands.
Hanford Hanford Laboratories, Hanford Atomic Products 167
Operation, General Electric Co., Richland, Washington.
Ispra Joint Research Centre, EURATOM (European Atomic *
Energy Community), Ispra, Italy.
KEI Krzhizhanovskiy Energetics Institute, Moscow, USSR. 332
KIA Kurchatov Institute of Atomic Energy, Moscow, USSR. 197
MAN Maschinenfabrik Augsburg-Nurnberg, Nuremberg, Federal 90
Republic of Germany
MEI Moscow Power Institute, Moscow, USSR. 101
ORNL Oak Ridge National Laboratory, Oak Ridge, Tennessee. 462
PNL Pacific Northwest Laboratory, Battelle 162
Memorial Institute, Richland, Washington.
SORIN Societa Ricerche e Impianti Nucleari, Saluggia, Italy. 676
SRL Savannah River Laboratory, E.I. Ou Pont Nemours and 294
Co., Aiken, South Carolina.
Tokai Tokai Research Establishment, Japan Atomic Energy 284
Research Institute, Japan.
Total 12473
*Some of the tests attributed to SORIN were
performed at Ispra.
13.2 Names of Reactor Concepts and Designs
CIRENE CISE Reactore a NeLbia (CISE Fog-cooled Reactor) CISE, Milan,
Italy.
BHWR Boiling Heavy Water Reactor.
46
LWBR Light Water Breeder Reactor, Westinghouse Electric Corp.,
Pittsburgh, Pennsylvania.
SGHWR Steam Generating Heavy Water Reactor, United Kingdom Atomic
Energy Authority.
47
TABLES 1-31 ; GENERAL COMMENT
Tables 2A and 2B each occupy four pages; they are arranged so that thefirst page of Table 2A can be read in conjunction with the first of Table 2B,
and so on. Other tables are set out in the conventional manner.
48
TABLE 1
COMPILATIONS OF BURNOUT DATA FOR AXIAL FLOW OF WATER THROUGH
ROD BUNDLES AND ANNULI
Reference
Macbeth [1964]
Harriett [1966]
Barnett [1968]
Tong et al.
[1964]
Hughes [1970b]
Hughes et al.
[1974]
Mironov et al.[1978]
This work
Rod Bundles
No. of
Assemblies
23
26
40
18
20
126
76
297
No. of
Tests
459
727
1007
366
735
4277
~6000
11203
Annuli
No. of No. of
Assemblies Tests
-
i23 ' 724
29 830
>
34 ' 953
-
- -
?
_ _
24 1270
Remarks
6.9 MPa (1000 psia) only.
Updating of Barnett (1966) ,
numbers for which are included.
6.9 MPa (1000 psia) only.
DNB Data Library; also
included a large amount of data
for round tubes.
Pressures between 1 and 5 MPa.
Organised for computer use;
available as part of EKREST
program package [Lintner 1970] .
Organised for computer use.
Organised for computer use.
49
NOTES TO TABLE 2A
1. -0., -0.0, -0.00, and -0.000 indicate that the item is not applicable orthe information is not given in the source of data.
2. Data source references (col.2) are listed in Section 10.2.
3. The meanings of symbols used to indicate special features (col.3) aregiven in Table 2C.
4. The number of grids (col.16) includes only those occurring in the heatedlength of the channel.
5. The meanings of grid type reference numbers (col.17) are given in Table2D.
6. The symbol '&' following a grid type reference number (col.17) indicatesthat different grid types are used in the same assembly. The number of
grids is the total number of all types, but only the principal typereference number is indicated.
7. Confidential information has been omitted from the table.
50
TABLE 2A
MAIN CHARACTERISTICS OF TEST ASSEMBLIES
ASS. DATA
SRCE
REF.
1
2
3
4
5b
7
89
10
11
13
14
15
16
17
18
19
20
21
22
23
24
24
25
25
25
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
55
64
65
66
67
68
69
70
71
72
73
7*
75
76
77
78
79
80
81
d2
83
84
85
86
87
88
89
90
1
2
2
3
45,6
7
8
9
9
9
9
9
9
9
9
9
11
11
12
12
12
12
12
12
12
U
12
13
14
14
15
16
16
16
17
17
17
17
18
11
19
19
20
20
20
20
20
21
21
21
21
21
21
20
20
20
12
12
12
12
12
12
25
25
18
17
14
26
26
27
27
5
2U
29
30
31
31
32
32
32
32
32
32
SPECIAL NO.
FEATRS OF
RODS
X
?n
?7x*
7
?*
??
Xt
Xxt
xtxt
xtxt
xtxt
X
7
7
7
+4
X*
X*
7
7
7
7
7
7
7
7
7
7
7
X
X
X
Xt
Xxt
xtxt
xt
4?
?4
?M
?7
?4
?4
+ ?*
? 4*
?<*
???
*4*t
?4?t
3.
4.4.
19.
19.
7.
12.
7.
19.
19.
19.
19.
19.
19.
19.
14.19.
9.
9.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
6.
7.
37.
7.
6.
7.
19.
19.
19.19.
19.
9.
3.
3.
7.
7.
7.
7.
7.
7.
7.
7.
7.
7.
7.
3.
3.
3.
3.
3.
3.3.
3.
3.
1.
1.
19.
19.
6.
19.
19.
9.
9.
7.
19.
37.
37.
9.
9.
2.
2.
2.
2.
2.
2.
sec
OIAM.
6.35
11.11
11.11
13. S7
13. ?713. S7
11. Id
12.70
IS. ?7
15.87
15. b?
15.87
15.87
15.87
15.47
15.87
15.67
11.11
11.11
10. Cl
10. Cl
10. Cl
10.01
10. Cl
10.01
10. Cl
10. Cl
10. Cl
13.80
13.80
13.80
13.80
10.00
10. CO
10.00
19.41
19.81
19.81
19.41
15.54
11.11
17.70
12.70
10.20
10.20
10.20
10.20
10.20
10.23
10.20
10.23
10.20
10.20
17.95
5.01
5.01
5.01
10. C6
10.Ce10.06
10. C6
10. C6
10.06
10.20
10.20
15.54
19.81
13.90
19.61
IS. 74
9.52
S.52
13.97
13.97
13.80
13.80
10.20
10.20
10.20
10.20
10.20
10.20
10.20
10.20
ROD ROD t-EATEO L5MGTH HEATO/
GAP PITCH LENV.TH /HEATO nETTED
/31AM. EJ.D1A PKUM.
1.57
4.J5
4.75
2.11
2.11
2.11
0.562.54
2.2C
2.64
2.2C
2.84
2.2C
2.84
2.2C
2.20
2.64
4.75
4.75
6.40
6.4C
6.40
6.4C
6.40
6.4C
6.40
6.40
6.4C
8.80
11. 6C
7.8C
7.83
4.00
4.03
4.0C
1.02
1.02
1.C2
1.02
1.02
4.75
3.S4
5.51
3.8C
3.80
3.dC
3.80
3.80
3.80
2.2C
1.25
1.25
1.25
1.38
2.00
2.00
2.00
6.40
6.40
6.40
6.4C
6.40
6.4C
-O.OC
-O.OC
1.02
1.02
11.50
1.02
0.97
4.78
4.78
2.11
2.11
7.80
7.80
3.20
3.20
3.20
3.2C
3.20
3.20
3.23
3.2C
1.248
1.427
1.427
1.151
1.151
1.151
1.050
1.200
1.138
1.179
1.1381.179
1.138
1.179
1.138
1.138
1.179
1.427
1.427
1.639
1.639
1.639
1.639
1.639
1.639
1.639
1.639
1.639
1.6381.041
1.565
1.565
1.400
1.430
1.400
1.051
1.051
1.051
1.051
1.065
1.427
1.3101.434
1.3731.373
1.373
1.373
1.373
1.373
1.216
1.123
1.123
1.123
1.077
1.399
1.399
1.399
1.636
1.636
1.636
1.636
1.636
1.636
-0.000
-0.000
1.065
1.051
1.827
1.051
1.049
1.501
1.501
1.151
1.151
1.565
1.565
1.3141.314
1.314
1.314
1.314
1.314
1.314
1.314
1372.
1219^
914.
182V.
940.
432.
1629.
1219.
12X9.1219.
1219.
1219.1219.
1219.
1219.
1219.
7b2.
7b2.
?iiS.
d3S.
835.
635.
835.
d35.
835.
d35.
835.
4000.
4420.
4380.
4375.
3000.
3000.
3000.
457.
889.
1829.
2743.
1930.
Ii24.
4521.4521.
407.
407.
1634.1634.
1634.
1634.
1630.
1600.
1634.
1634.
1645.
711.
686.
730.
635.
835.
835.
835.
635.
835.
1183.
560.
1S30.
1829.
4420.
2743.
2499.
457.457.
940.
914.
4365.
4365.
1183.
1183.
S90.
590.
590.
590.
590.
590.
70.1
-.60
61.9
95.0
1H9.<4
113.7
157.2
116.1 '
112. a
?J7.3
112.8
97.0
112. d
97.0
112.6
9U.ii
96.5
39.1
39.1
44.1
Id.i)
44.1
44.1
44.1
44.1
4H.1
44.1
44.1
76.5
93.9
103.7
119.5
148.3
118.7
127.1
53.5104.3
213.9
320.8
256.4
78.2
200.3
200.3
21.4
21.4
dS.d
85.8
35.8
d5.8
140.!
210.5
241.8
175.3
163.0
64.7
62.4
64.0
59.0
27.3
59.0
59.0
59.0
59.066.1
31.3
2S6.4
213.9
95.0
303. V
267.2
20.0
20.0
102.0
95.0
119.3
119.3
96.9
80.8
12.023.9
23.9
23.9
35.9
35.9
C. 461c. SJH
0.538
5. .'53
C. 783
0.6<>5C. 730
0. 5'jt>
0.7U1
0. 727
D.7?l
0. 7^7
3.781
0.727
0.781
3. 7<>4
C.7?4
O.t3l
C. 631
1. JOO
0, 426
1.303
l.uOOI. 000
1.030
1.000
1.303
1.000
0.442
0.53H
0.476
0.735
0.603
0.566
0.517
0.705
0.785
C.785
0.7H5
0.782
0.631
0.498
0.498
0.610
0.610
C.610
0.610
0.610
0.610
0.644
0.667
0.689
0.673
0.679
0.492
0.402
0.489
1.000
0.463
1.000
1.000
1.000
1.000
0.348
C.348
0.782
0.785
0.540
0.743
0.742
0.602
0.602
0.638
0.783
0.735
0.735
0.642
0.630
C.177
3.354
0.354
0.354
0.531
0.531
1 10*
APti
.'93.tint.
bar.
2215.
<!?15.6B7.
304.?,? }.
277o.
^R2t .27r?.
2621.
2778.
.?ili'l .
277s.,/77<f.
211-1.
li?l.
1531.
1047.
1047.
1047.
1047.
1047.
1047.
1047.
1047.
1047.
1700.
3062.
2748.
1424)2.
1112.
1191.
1112.
2528.
2528.
2528.
252B.
1746.
1531.675.
675.
1068.
1068.
1068.
1068.
1060.
1068.
652.
426.
419.
578.
996.
130.
130.
135.
725.
725.
725.
725.
72?.
725.
143.
143.
1746.
2528.
3049.
2528.
2610.
1540.
1540.
708.
2215.
14282.
14282.
861.1056.
395.
395.
395.
395.
395.
395.
MtO'C
t-iUiV.
01AM.
i :?!>??11.50
7.!>4
7.54
a. 21<f.31
a. 75
9.45
s.13
0.<O
9.13
3.45
9.13
d.45
d.96
S.96
12.31
12. il
18.92
1H.92
10. "?2
16.92
13. 92la. 92
13.92
13.92
16.92
23.0?
25.35
20.13
26.09
12.21
14.30
12.21
6.7i
6.71
6.71
6.71
5.88
12.31
11.24
11.24
11.62
11.'?
11.62
11.62
11.62
11.62
7.48
5.07
4.66
6.27
6.85
5.41
5.41
5.58
14.16
14.16
14.16
14.16
14.16
14.16
6.23
6.23
5.88
6.71
25.14
6.71
6.94
13.76
13.76
5.88
7.54
26.89
26.89
7.84
9.22
8.73
8.73
8.73
8.73
b.73
8.73
HJtTHJ
fc M I V .
ill AM.aa.
19.48
1 -/.oa
1't.bA
?i.ci
??.o3
7.9?
2.75
15.75
IJ.Sl
12.5710. dl
U.57
lO.dl
12.57
10. al
12.3(1
12. 3S
19.4-.l-y.49
Id. 92
4t.40
lo.tZ
Is. 92
la. 92
18.92
Id. 92
ld.92
Id. 92
52.27
47.00
42.2s
36.60
20.23
25.27
23.60
8.55
8.5S
3.1.5
d.5S
7.53
19.49
22.57
22.57
19.05
19.05
19.05
19.05
19.05
19.05
11.62
7.60
6.76
9.3210.09
11.00
11.0011.41
14.16
30.60
14.16
14. Ib
14.16
14.16
17.89
17.89
7.53
8.55
46.54
9.03
9.3S
22.87
22.87
9.22
9.63
36.60
36.60
12.21
14.64
49.33
24.66
24.66
24.66
16.44
16.44
"ADI AL
(?JAM
??ACT J*
1.330
U370
1.131
I.lu3
I.lo7
1.030
l.OJO1.227
U143
1.3-.7
l.US
1.213
1.112
1.4.VO
1.105
1.1ft
1.000
1.112
1.023
1.000
1.679
1.514
1.291
1.191
1.169
1.142
1.109
1.000
1.000
1.003
1.000
1.303
1.000
1.000
1.117
1.125
1.117
1.141
1.077
1.070
1.000
1.030
1.000
1.385
1.000r.ooo
1.000
1.300
I. 000
1.000
1.072
1.0721.000
1.000
1.000
1.000
1.016
1.000
1.089
1.560
1.201
1.395
1.000
1.000
1.077
1.119
1.000
1.107
1.111
1.154
1.369
1.005
1.124
1. 180
1.098
1.000
1.000
1.000
1.246
1.093
1.017
1.567
1.122
MutCSU
l.OJO
1.300
1.303
1.000
l.OJO
1.003
l.uOO
1.000
1.000
1.300
1.030
1.300
1.300
1.300
1.000
1.000
1.000
I. 000
1.000
1.030
1.000
1.030
1.000
1.300
1.000
1.300
1.000
1.000
1.300
1.000
1.000
1.000
1.30J
1.000
l.OJO
1.000
1.000
1.000
1.003
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.223
1.000
1.000
1.000
1.000
1.000
1.185
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.030
NO. 6*10
Of TfPEr.?ins
3.
4.
4.
d.
4.
i.
4.
6.
13.6.
5.
fe.
10.).
to.
13.
2.
2.
-0.
-3.
-0.
-0.
-3.
-0.
-0.
-0.
-0.
-0.
4.
4.
7.
-0.
-0.
-0.
2.
4.
d.
12.
7.
2.
19.
IV.
0.
0.
3.
4.
3.
3.
3.
3.
7.
7.
3.
6.
6.
7.
-0.
-0.
-0.
-0.
-0.
-0.
3.
1.
31.24.
4.
12.
-0.
2.
2.
1.
4.
7.
7.
5.
5.
2.
2.
2.
2.
2.
2.
4.3 4
1.2
2.0
2.C
2.0
2.0
4.2
1.0
5.0 i
1.0
5.0
2.C
10. C J
2.0
8.0 1
7.0 &
3.2 1
3.2 t,
-O.C
-0.0
-O.C
-0.0
-O.C
-0.0
-0.0
-0.0
-0.0
-O.C
7.0
7.0
7.0
-0.0
-O.C
-0.03.;
3.2
3.2
3.2
3.2
3.2 t
3.4
3.4
0.0
0.03.4
4.3 &
4.3
3.4
3.4
3.4
3. 1 i
3.1 i
3.4
4.2
4.2
3.4
-0.0
-0.0
-0.0
-0.0
-0.0
-0.0
3.1
3.1
3.2 4
3.2 <
7.0
3.2
-0.0
6.2
6.2
4.1
2.0
7.0
7.0
5.0
S.C
3.1
3.1
3.1
3.1
3.1
3.1
51
TABLE 2B
NUMBER AND RANGE OF BURNOUT TESTS WITH EACH ASSEMBLY
ASS.
1
2
3
4
5
6
T
8
?*
10
11
13
14
15
16
17
18
19
20
21
22
23
24
24
25
25
25
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
55
64
65
60
67
68
69
70
71
72
73
74
75
76
77
78
79
80dl
02
?3
d4
85
86
87
88
89
40
NO.
OF
TESTS
15.18.
27.
4.
44.
5.
51.
18.
40.
9.
19.
15.
15.
12.
16.
6.
12.
13.
30.
36.
89.
13.
11.
1.
2.
2.
2.
2.
39.
6.
21.
16.
30.
21.
26.
12.
54.
41.
32.
38.
59.
44.
15.
27.
22.
70.
14.
21.
14.
A3.
68.
51.
42.54.
94.
9.
20.
34.
56.
17.
20.
15.
5.
45.
62.
25.
20.
3.
24.
45.
22.
5.
3.
13.
38.
B2.
57.
178.
20.
5.
4.
14.
5.
5.
PRrSSuiU
Ri.Not
fFA
6. 895: 6.39'j
6.895: 6.8*5
6.895: 6.8<5!>
6.895: 6.895
6.S93: 6.9S3
O.U*6: 6.SS1)
6.274: 4.274
6.89s: 6.3')s
6. ?53: o.hSS
6. 729: 6.695
6.695: b.S',1
6.805: 6.895
6.819: 6.895
6.791: 6.80?
6.fi2o: 6.895
6.6)3: 6.8V5
6.7d4: 6.874
6.695: 6.89*
6.895: 6.8S5
1.520: 4.020
1.010: 4.5oO
1.570: 4.C20
2.C6Q: 4.020
?.<4C: 2. tO
3.040: 3.040
3.C40: 3.C40
3.C40: 3.C40
2.840: 3.430
3.040: 4.510
5.000: 5.010
1.270: 5.020
4.950: 5.010
3.040: 6.960
3.040: 5.000
3.040: 6.960
6.8oO: 8.267
3.337: 8.274
3.316: 8.274
3.261: 8.239
6.895: 8.274
4.137: 9.653
4. 137: 9.653
6.895: 6.895
4.950: 5.000
4.990: 0.480
4. 980: 6.520
5.020: 5.030
5.000: 5.090
6.476: 6.997
5.C06: 7.066
5.C36: 7.232
5.C84: 7.297
5.C54: 7.117
5.032: 7.110
5.090: 8.940
4.970: 8.890
7.COC: 7.130
1.570: 3.680
1.570: 3.733
1.570: 3.580
1.520: 3.530
1.570: 3.480
2.550: 3.530
3. 187:13. C72
3.256:13.190
6.895: 6.895
3.303: 8.246
5.030: 5.130
3.447: 8.274
5.171: 8.274
6.895: 9.756
6.874: 6.929
6.860: 6.895
6.881: 6.895
3.000: 8.730
2.960: 6.S70
8.430:14.460
7.890:15.610
12.750:13.140
13.140:13.340
17.850:13.140
5.150:13.340
12.750:13.290
12.940:13.140
?A3S FLUX
PA?4C-E
,,?-'S.SSM.. . -,_44. 02: ICO. 50
23. ?/: 129.11
27.60: 2C7.3766.59: 68.76
66.46: 272.6072. S&: 215.04
65.10: 554.70
78.66: 204.79
',5.26: 345. B4
63. Gd: 203.43
6i?.3!>: 347.19
32. 5i: 2C0.72
o5.)3: 26d.53
60. to: 1'64.46
61. 14 J 337.70
l>5.10: 265.82
<>5.10: 269. d9
66.86: 138. 8d
40.69: 173.469.55: 14.02
3.41: 54.41
15.66: 24.54
17.57: 22.6321. B7: 21.87
10.03: 10.22
10.12: 10.12
10.12: 10.53
11.17: 11.54
19.63: 93.40
54.20: 148.50
35.60: 22d.70
36.00: 1C7.20
21.00: 117.70
22.80: 94.10
26.30: 104.80
67.81: 268.53
13.56: 410.94
13.56: 406.87
13.56: 271.25
136. 9d: 410.94
65.91; 172.92
33.23: 136.17
66.59: 135.76
107.00: 222.00
109.00: 222.00
74.00: 222.00
108.00: 112.00
108.00: 221.00
78.61: 151.50
76.75: 383.90
79.05: 387.20
79. Od: 384.60
79. f2: 387.40
79.15: 369.00
109.00: 251.00
109.00: 110.00
110. 00: 151.00
14. <<3: 43.08
8.64: 49.70
15.00: 25.40
18.17: 34.41
20.10: 39.50
12.76: 34.90
91. HO: 403.00
68.50: 418.50
141.05: 410.94
13.56: 404.16
51.20: 102.20
27.12: 271.25
135.62: 271.25
75.27: 154.61
75.27: 76.70
69.17: 191.23
67.81: 271.25
42.01: 178.90
19.70: 136.60
46.40: 226.50
41.40: 3C9.00
50.10: 230.00
50.30: 221.40
50.00: 227.70
49.40: 224.60
135.50: 151.00
135.00: 141.00
INLET JUAUTY
RANGE
-0.220:-0.054
-0.468:-0.047
-0.429:-0.022
-0. 102:-0.040
-0.499:-0.040
-0.238:-0.061
-0.6?6:-0.000
-0.089:-0.003
-0.324:-0.02d
-0. 179:-0.019
-0. 329:-0.038-0.259:-O.OsO
-0.255:-O.C41
-0.255:-0.03o
-C.260:-O.C45
-0.196:-0.046
-0.2S5:-0.031
-0.285:-0.025
-C.420:-3.020
-0.391:-0.171
-0.407:-0.126
-0.38d:-0.171
-0.359:-0.214
-C.269:-0.269
-0.306:-0.30l
-0.308:-0.306
-0.306:-0.294
-0.337:-0.286
-0.230: -0.046
-0.028:-0.008
-O.C87:-0.008
-0.072:-0.010
-0.575:-0.212
-0.435:-0.187
-0.563:-0.262
-0.327:-0.02d
-0.327:-0.022
-0. 31S:-0.020-0.326:-0.021
-0.579: 0.391
-0. 342:-0.011
-0.283: 0.019
-0.257:-0.033
0.036: 0.608
-0.254:-0.01S
-0.347: 0.613
-0. 143: 0.598
-0.190: 0.609
-0.25U-0.Otil
-0.276: 0.497
-0.224: 0.412
-0.217: 0.508
-0.207: 0.057
-0.199: 0.420
-0.154: 0.698
0.021: 0.321
0.135: 0.857
-C.276:-0.113
-0.447:-0.089
-0.284:-0.134
-0.288:-0.079
-0.275:-0.131
-0.215:-0. 162
-0.696: -0.040
-0.699:-0.006
-0.504: 0.190
-0.323:-0.023
-0.038:-0.031
-0.324:-0.023
-0.197: 0.189
-0.072: 0.233
0.008: 0.173
-0.054:-0.046-0.32l:-0.049
-0.086:-0.007
-0. 189:-0.008
-0.448S-0.029
-0.604:-0.018
-0.446:-0.103
-0.429:-0.273
-0.4S2:-0.290
-0.448:-0.030
-0. 374:-0.098
-0.415:-0.015
BURNOUT OUAL1TY
RANGE
0.204: 0.339
0.090: 0.461
0.099: 0.539
C.380: 0.417
0.178: 0.496
0.179: 0.439
-O.J20: 0.524
0.225: 0.427
0.017: 0.647
0.124: 0.4ol
0.013: 0.347O.lSti: 0.661
0.050: 0.374
0.200: 0.479
0.064: 0.383
0.022: 0.408
0.155: 0.521
0.101: 0.290
0.036: 0.393
0.589: 0.727
0.060: 0.849
0.227: 0.328
0.322: 0.4050.413: 0.418
0.719: 0.731
0.740: 0.743
0.735: 0.762
0.670: 0.078
0.214: 0.486
0.220: 0.404
0.116: 0.448
0.226: 0.515
0.222: 0.595
0.242: 0.641
0.219: 0.569
-0.127: 0.224
-0.077: 0.777
0.049: 0.914
0.254: 0.983
-0.143: 0.618
0.137: 0.415
0.204: 0.785
0.191: 0.478
0.119: 0.638
-0.131: 0.150
0.123: 0.088
0.250: 0.652
0.192: 0.652
O.loO: 0.322
0.114: 0.020
0.095: 0.622
O.llo: 0.646
-0.033: 0.3780.168: 0.606
0.192: 0.733
0.262: 0.454
0.395: 0.877
0.393: 0.717
0.137: 0.469
0.608: 0.780
0.291: 0.446
0.343: 0.535
0.336: 0.373
-0.405: 0.211
-0.445: 0.156
0.105: 0.560
0.138: 0.835
0.259: 0.403
0.263: 0.855
0.3C7: 0.483
0.011: 0.330
0.140: 0.260
0.210: 0.375
0.090: 0.344
0.181: 0.489
0.246: 0.735
-0.006: 0.499
-0.113: 0.533
-0.364:-0.005
-0.246:-0.045
-0.282:-0.077
-0.263: 0.104
-0.186: 0.024
-0.148: 0.130
BURNOUT HFAT
FLUX RANGE
a/sacfl _
113.2: 187.4
124.6: 345.1
117.0: 324.0
120.1: 130.1
79.8: 231.0
122.0: 195.5
84.7: 404. C
123.6: 191.8
97.9: 259.6
150.4: 266.4
98.0: 235.6
102.9: 294.6
116.0: 244.1
157.1: 275.3
118.8: 265.9
125.5: ?46.1
163.9: 265.1
21b.7: 301.9
191.2: 3o2.1
94.9: 125.5
88.2: 306.3
192.6: 201.2
193.1: 199.7
197.6: 197.0
125.9: 125.9
83.1: 83.1
8S.7: 88.7
96.3: 96.6
72.7: 150.4
102.5: 150.3
61.4: 151.4
65. 0: 103.2
60.0: 166.4
84.7: 181.2
86.8: 180.5
125.8: 244.2
30.8: 277.7
17.4: 161.2
19.2: 113.2
39.7: 174.8
130.9: 331.5
45.1: 108.8
67.2: 114.5
61.8: 318.8
326.9: 525.1
25.0: 237.5
27.7: 204.3
22.5: 218.8
143.9: 231.9
28.4: 256.1
32.7: 227.3
40.8: 217.7
59.1: 207.4
51. 1: 151.9
22.2: 324.4
91.8: 161.4
15.5: 201.6
102.7: 190.9
100.0: 304.0
99.6: 145.0
144.5: 194.0
141.3: 191.3
189.8: 191.3
103.9: 492.8
146.0: 710.5
66.8: 172.4
IB. 8: 164.5
97.1: 127.8
32.8: 122.9
73.1: 147.1
145.1: 271.3
173.5: 258.7
107.0: 177.3
137.0: 314.1
85.7: 127.0
35.8: 96.2
86.9: 183.3
99.9: 278.5
178.8: 444.8
221.6: 395.7
245.0: 437.9
179.3: 450.2
203.2: 335.5
172.6: 320.1
52
TABLE 2A (CONTINUED)
MAIN CHARACTERISTICS OF TEST ASSEMBLIES
ASS. DATA
SRCEREF.
91
92
93
94
96
97
98
99
100
101
101
101
102
102
102
103
103
103
104
104
104
105
105
106
107
108
109
110
111
112
113114
115
116
117
118
119
120
121
121
122
123
124
125
126
127
128
129
130
131
132
133134
135
136
137
138
139
140
141
142
143144
145
146
147
146
149
150
151
152
153
154
155
156
157
158159
160
161
162
163
164
32
32
32
33
^*?Jj
33
3333
3312
1212
1212
12| y
12
12
12
12
12
12
12
12
12
12
12
12
12
12
13
34
35
36
36
36
36
37
37
38
38
38
38
39
39
36
4041
41
39
39
40
40
40
40
42
43
11
11
44
45
46
47
47
48
47
49
49
49
45
50
50
50
49
49
49
51
51
51
52
53
52
53
52
SPECIAL NO.
FEAIRS OF
RODS
???*$
???*
**?*
?*?
a9
*?
?.,
xxs
X*xs
X*xs
xsxs
xsxs
xsxs
xsxs
xs
X
X
X*
7
7
7
X
+?>???
?<*?
?<*?
+??*
m
>rf
?*
EL+*
?M?*
*?
?*?*
?*?*
*
?
*
?
??tn
nt
tt*
**
*sctl
??c
????c
N7>l
N7<|
N7<l*?c
??c**c
???*
Xx?
X*
X*l
X*x?*
2.
2.
2.
9.
*
9.
9.9^
9.
3.
3.
3.
3.3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
7.
7.
7.
3.
9.
9.
16.
16.
16.
16.
21.
21.
16.
16.
16.
16.
9.
9.
16.
19.
20.
20.
9.
9.
19.
19.
19.
19.
19.
19.
9.
9.
19.
9.
16.
1.
1.
2.1.
4.
4.
4.
4.
7.
7.
7.
4.
4.
4.
9.
9.
3.
20.
7.
20.
7.
20.
RCD
01 AH.
MM
10.20
10.20
10.20
10.20W
7A? Zw
10.20
10.20
10.20
10.2010. CO
10. CO10. C6
10. C6
10.06
10. C6
10. Co
10. Co
10. C6
10. C6
10.06
10. C6
10.06
10. C6
10. C6
13.00
13. CO
13.00
10.00
10. CO
10. CO
13.80
10.67
10.67
14.29
14.29
14.29
14.29
10.72
10.72
14.29
14.29
14.29
14.29
14.48
14.48
14.29
14.33
12.70
12.70
14.48
14.48
15.58
14.91
14. ?
14.41
14.33
14. SI
14.48
14.46
14.91
14.33
14.27
12.70
14.33
11.11
12.70
10.00
10.00
10.00
10.00
12.70
13.25
13.25
10.00
10.00
10.00
11.70
11.70
13.80
19.CS
5.00
19. C5
5. CO
19.05
ROD
GAP
MM
3.20
3.20
3.2C
3.2C
3 j P*cw
3.2C
3.2C
3.20
3. 20
6.40
6.4C
6.40
6.4C
6.4C
6.4C
6.4C
6.40
6.4C
6.4C
6.40
6. 40
6.40
6.4C
6.40
2.CO
6.CC
6.0C
6.00
6.0C
6.00
7.80
3.51
3.51
4.46
4.46
4.46
4.46
3.40
3.40
3.33
3.33
3.33
3.33
4.27
4.27
4.46
1.88
4.19
4.19
4.27
4.27
0.38
1.27
1.27
1.27
1.88
1.27
4.65
4.65
1.27
4.42
4.44
-O.CC
-O.CC
4.75
-O.CC
3.50
3.50
3.50
3.50
10.30
9.75
4.75
3.50
3.50
3.50
14.3C
14.30
6.80
0.38
1.70
0.38
2.75
0.38
ROD HEATED LENGTH HEATD/
PITCH LENGTH /HEATH .CTTEI)
/OIAH. E3.0IA PER1M.
1.314
1.314
1.314
1.314
1 114? J **t1.314
1.314
1. 3141.314
1.636
1.636
1.636
1.636
1.636
1.636
I.o3o
UO.-6
1.636
1.630
1.036
1.636
1.636
1.636
1.154
1.462
1.462
1.590
1.596
1.590
1.565
1.329
1.329
1.312
1.312
1.312
1.312
1.318
1.318
1.233
1.233
1.233
1.233
1.295
1.295
1.312
1.1311.330
1.330
1.2V51.295
1.024
1.085
1.0E5
1.085
1.131
1.085
1.321
1.321
1.085
1.309
1.311
-0.000
-0.000
1.427
-0.030
1.353
1.350
1.353
1.350
1.811
1.736
1.736
1.350
1.350
1.350
2.222
2.222
1.493
1.020
1.340
1.020
1.550
1.020
590.
590.
590.
1183.
1183.
1143.
1 183.
1143.
1670.
1670.
1670.
Io70.
1670.
1670.
1670.
1670.
1670.
1670.
1670.
1670.
1070.
1670.
1670.
830.
630.
830.
1670.
1670.
1670.
4440.
1829.
1829.
1829.
1829.1829.
1829.
1524.
1524.
1829.1829.
1829.1829.
1829.
1829.
1429.
470.
2433.
2438.
1829.
1829.
495.
495.
495.
1943.
495.
1930.
1829.
1829.
4VS.
1829.
3658.
1219.
1219.
762.
1219.
1700.
1900.
1900.
1900.
1600.1600.
1600.
1900.
1900.
1900.
1700.
1700.
4000.
2388.
500.
2388.
500.
2388.
47.8
47.0
47. H
74.0
44. V
46.3
80.8
40.3
54.0
117.9
117.9
117.9
117.*
117.9
117. V
117.'*
117.9
117.9
117.9
117.5
117.9
117.9117.9
27.0
27.0
34.5
65.8
34.7
19.5
90.6
136.0
136.0
VV.l
99.1
99.1
99.1
93.4
93.4
115.1
115.1115.1
115.1
94.594.5
99.1
44.5
134.6
134.6
94.5
94.579.4
55.05U.O
227.44u.9
225.9
94.0120.3
46.69o.4
195.995.7
148.331.5
159.6107.7
137.726.9
107.737.7
40.440.4
107.7107.7
107.723.4
25.481.6
539.170.3
539.170.3
721.0
S.7C80.7C8
0. JOo
0.553
3.350
0.3oo
3. 630
0.346
0.463
.000
.000
. oOO
.303
.030
.000
. 530
.000
.000
.000
.000
.000
1.000
1.000
0.486
0.486
0.309
0.585
0.524
0.462
0.448
0.639
0.639
0.711
0.711
0.711
0.711
0.717
0.717
0.713
0.713
0.713
0.713
0.653
0.653
0.711
0.767
0.716
0.716
0.653
3.653
0.793
0.774
0.816
0.416
0.767
0.834
0.648
0.664
0.774
0.650
0.711
0.313
0.340
0.423
0.522
0.539
0.539
0.135
0.539
0.559
0.570
C.570
0.539
0.539
0.539
0.501
0.498
0.448
0.773
0.618
0.773
0.618
0.737
FLO.
4AEA
3SS.
3"?i>.
31*1).1C24.
iC5t..1024.
1024.
725.
725.
725.
725.
725.
725.
725.
725.
725.
725.
725.
725.
725.725.
9*1.
941.
730.
1403.
2661.
4725.
1594.
1014.
1014.
3314.
3314.
3314.
3314.
2885.
2685.
2851.
2851.
2851.
2ES1.
1980.
1960.
3314.
2257.3614.
3614.
1980.
1960.
1510.
2004.
2004.
2004.
2258.
2C04.
1991.
1556.
2258.
1921.
3348.
127.
93.
422.
127.
554.
554.
554.
554.
2962.
2883.
2683.
554.
554.
554.
6014.
5538.
1594.
1325.
195.
1325.
195.
991.
MYC?C
FOUlv.OJAM.
0. il
8.7)
a. 73b.b4
?).2?:
0.64
8.8*
14.10
14. lo
14.10
14. lo
14.16
14.1o
14.10
14.10
14.10
14.10
14.16
14.10
14.1o
14.16
14.93
14.93
8.80
14.44
25.2039.47
21.97
8.59
B.5-J13.13
13.13
13.13
13.13
11.70
11.73
11.32
11.32
11.32
11.32
12.63
12.63
13.13
8.10
12.96
12.96
12.63
12.63
4.94
6.97
0.97
0.97
8.10
7.13
12.61
10.09
7.86
12.34
13.27
3.99
2.79
10.22
3.99
9.51
9.51
9.51
9.51
23.73
22.56
22.56
9.51
9.51
9.51
36.44
33.31
21.96
3.42
4.39
3.42
4.39
2.44
ifATEi)
12.33
12.13
U.33
li.vo
20.35
2S.57
^5.57
sO?oH
14.16
1-..16
14.10
14.1o
14.16
14.10
14.16
U.lo
14.101-..16
14.10
14.16
14.16
30.74
30.74
24.34
25.37
48.11
85.42
49.03
13.45
13.45
14.46
16.46
18.4o
14.46
16.32
16.32
15.88
15.88
15.88
15.88
14.35
H.3S
111. 40
10.56
18.12
18.12
19.35
19.356.24
?4.014.55
0.55
10.56
8.55
19.45
15.2110.15
18.97
18.67
12.74
8.22
24.16
7.64
17.64
17.64
70.55
17.64
42.42
39.58
39.58
17.64
17.64
17.64
72.71
66.96
49.02
4.437.11
4.43
7.11
3.31
PADIALF.iPI
FACT.K
1.763
1.501
1.133
1.000
1. OBI
1.041
1.000
1.000
1.701
1.023
l.tol
1.452
1.340
1.236i.m
1.120
1.043
1.034
1.003
1.042
1.09O
1.000
1.030
1.000
I. 000
1.000
1.000
1.000
1.000
1.000
1.300
1.000
1.000
1.250
l.ObO
1.066
1.320
1.320
1.320
1.320
1.000
1.030
1.250
1.067
1.500
1.003
1.000
1.000
1.010
1.030
1.335
1.048
1.069
1.046
1.000
1.030
1.000
1.003
1.003
1.030
1.000
1.000
1.414
1.000
2.294
1.003
1.2831.004
1.029
1.029
1.403
1.187
2.160
1.000
1.000
1.000
1.500
1.000
1.500
1.000
1.500
AXIAL
FACtUV
1.000
1.303i.:oo
1.0 JOIftnn
?Uwv
I. 000
1.300
1.728
1.000
1.000
1.000
1.000
1.300
1.000
1.030
I. 000
1.000
1.000
1.003
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.160
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.387
1.000
1.000
1.000
1.000
1.000
1.300
1.000
1.000
1.245
1.368
1.368
1.000
1.000
1.000
1.000
1.000
1.473
1.000
1.030
1.000
1.000
1.000
SO. CA 10
OF TYPE
GRIDS
2.
2.?.
.
5.
5.5,
3.
-0.
-0.
-0.
-0.
-0.
-0.
-3.
-0.
-0.
-0.
-0.
-0.
-0.
-0.
-0.1.
I.1.
4.
4.
4.
-0.
3.
5.7.
4.
3.
7.
5.
5.
7.
7.
6.
7.
4.
3.
3.
2.4.
4.
3.
4.
4.
4.
4.
8.
2.
8.
4.
4.2.
3.
8.
12.
12.
-0.14.
5.
5.
5.
5.
1.
1.
1.
5.
5.
5.-o.
-0.
-0.
23.
2.
23.
2.
23.
3.1
3.1
3.1
5.CC. f
3. l?
5.0
5.C
5.0
5.C
-O.C
-0.0
-0.0
-0.0
-3.0
-O.C
-0. C
-0.0
-O.C
-0.0
-3.C
-0.0
-0.0
-0.0
-0.0
4.2
4.2
4.2
12. C 4
12.0 4
12. C 4
-0.0
5.0
5.0
3.2
10.0
10. C
3.2
7.0
11.0
3.2
3.2
3.2 4
3.2
10.0
10. C
10.0
l.C
7.0
7.0
10. C
10.0
l.C A
1.0 A
1.0 i
l.C
3.2
1.0
3.2
3.2
3.2
10.0
10.0
4.1
4.1
-0.04.1
10. C
10.0
10.0
10.0
13.1
13.1
13.1
10.C
10.0
10.0
-0.0
-0.0
-0.0
3.5 .t
3.3
3.5 &
3.3
3.9 &
53
TABLE 23 (CONTINUED)
NUMBER AND RANGE OF BURNOUT TESTS WITH EACH ASSEMBLY
ASS.
0192
93
9i
95
90
97
98
94
100
101
101
101
102
102
102
103
103
103
1C*
134
104105
105
106
107
108
109
110
111
112
113
114
115
116
117118
119
120
121
121
1?2
123
124
125
126
127
128
129
130
131
132
U3
134
135
136
137
138
139
140
141
142
143
144
145
146
147
148
149
150
151
152
153
154
155
150
157
158
159
160
161
162
Ib3
164
NO.
CF
TESTS
4.
3.a.
41.
22.64.
34.
i4.
61.
44.
24.
6.
4.
15.
14.
6.
7.
13.
7.
3.
13.
2.
4.
4.
11.
38.
39.
40.
29.
25.
i.
81.
513.
5-..
46.
26.
26.
17.
32.
14.
26.
39.
15.
142.
121.
4.
14.
43.
60.
35.
34.
19.
17.ia.
21.
7.
IS.
35.
14.
19.
63.
50.4.
2.
65.
5.
23.
11.33.
2.
1.
5.
1.
2.3.
16.
A2.ia.
ID.
60.
160.
21.
37.
48.
FRESS'JSC
?1ANU
M?A
n.C93:U.343
17.70CU3.HC
12.J5C.-1 1.<J>0
7.E5C:n.tJO
12.S>0:14.2<.'0
12. 470: IS.-. -'0
4.220:U.:>*0
8.3-.0:l3.;j3
?.3*0:lS.<,/02.;?a: 4.o?:o
2.060: ' ;:^U
2.C60: 4.270
2.COO: 4.UO
2.0t>3: 4.SJO
?.Ci>0: 4.120
2.COO: 4.270
7.C&0: 4. |7?
2.C6C-- 4.270
2.0oC: '..2<:0
3.C40: 3.C4C
2.C6C: 4.270
3.C40: 4.020
2.C6C: 4.U'0
2.0608 4. ,.'20
0.300: 0.9S3
0.320: 0.-.70
3.270: 1.060
t.CBJ: ?..C2d
1.C-.0: 4.020
3.C40: 4.020
3.04C: 3.C-.C
13.594:16.656
6.657:16.9*6
4.137: s. 61*
4.U7: 3.6lrt
6.695: o.flVS
6.895: 6.<J<5i
4.545:10.342
5.171:10.34.!
6.895: 6.8S5
5.171: 6.a-?b
0.845: 6.8S5
6.695: 6.895
4.C8V: 9.784
4.123: 9.6736.8*5: 6.695
8.375: 8.375
8.274:13.790
a. 274M3. 790
6.8-iO: 6. 598
5.206: 7.205
8.375: 8.375
8.375: tt.375
8.375: b.375
8.375: 8.375
8.274: 8.274
8.377: 6.377
6. ?95: 6.899
6.895: 0.895
8.377: 8.377
5.440: 6.943
5.495: 6.957
0.895: 6.895
6.895: 6.695
4.137: 9.653
6. ?95: 6.895
13.750:13.750
13.730:13.730
6.860:13.730
13.I3CM3.730
2.E37: 2.837
0.365: 1.520
2. ?37: 2.837
6.E50: 6.8506.650: 6.850
6.860: 6.460
4. COO: 9.8006. COO: 9.300
3.040: 8.924
8.274:13.790
2.940:13.700
B. 274:13. 790
6.860: 6.860
8.274:13.790
14SS I-LUX
Vi'jGi
liiS.swca
1-.1.60: 156.00
I'jJ.oO: 156.30
H2.70: loC.90
?>C.CO: 24C.23???(.JO: 23.S.1G
??.!.;0: 300.40
50.HO: 234. SO
"U.13S :>?5.0046.20: 102. SO
18.40: 133.03
19. (.3: S2.01
21.34: 53.41
iV.tS: 4S.28
23. S1:: So.i7
2J.89J "JV.Oi
2t.lS: iS. 74
ll.^ls bt'.4-!
2b.?<?: Vi.t.0
,<d. 79: ?7.4?
3C.4S: bb.o2
27.51: 69.42
34.14: J5.10
)6.20: 38.27
*7.-.4: 39.92
7.6&: 20.37
3.t7: 35.. 17
7.60: 36.51
IV. So: b6. 14
7.B4: 43.81
6.6(1: 29.09
SJ.itO: 117.60
135.7t>: 4B,*.l7
26. tj: 492. ti
34. 4S: 174.55
14. 4i: 173.05
68.4*: 179.84
03.76: 174.55
201.40: 410.80
135.62: 4CS.58
o/.iJd: 243.71
67. *4: 244.26
66.32: 245.07
67.54: 246.16
33. 3o: 205.88
33.50: 169.53
103.21: 106.19
65.10: 397.38
16.95: 275.11
16. 95: 269.89
33.36: 169.26
33.C4: 153.30
67.81: 546.50
67.61: 545.20
67.81: 680.1)3
67.81: 410.94
67.81: 203.43
67.BI: 412.29
65.64: 164.65
61.30: 103. id
67.81: 679.47
32.83: 137.11
33.65: 136.04
135.62: 257.60
162.75: 189.37
64.56: 263.92
135.62: 311.93
48.90: 295.50
86.90: 174.60
127.10: 294.40
168.60: 221.00
55.80: 55.80
14.10: 54.80
29.90: 29.90
202.50: 202.60
16.- 10: 238.70
113.00: 225.10
106.40: 199.30
69.10: IS8.00
21.10: 98.80
20.21: 406.87
31.50: 493.50
69.03: 210.08
77.40: 167.00
34.58: 413.65
INLET JUUITYRANi'.E
-0.38?:-0.076
-0.3l9:-3.Cd5
-0.387:-3.109
-Q.o<>8:-0.043
-0.4C2:-0.117
-0.7/6:-0.1l6
-O.M8:-0.036
-C.!>40:-0.039
-C.(,OC:-0.038
-0.2?<?:-0.13d
-0. 307:-0.154
-I. 'I0o:-0.170
-O.?'7l:-0.204
-0.307:-0.178
-0. 3?4:-0.184
-0.273:-0.1-il
-0.26Vt-0.180
-C.312:-0.l7l
-0.2H2:-0.182
-0.280:-0.179
-0.370:-0.133
-0.249:-0.239-0.253:-0.204
-0.249:-0.232
-0.213:-0.130
-0.238:-3.124
-0.238:-0.118
-3.31l:-0.0oo
-0. 360:-0.0?2
-0.277:-0.120
-0.044:-0.028
-0.7oO:-0.073
-O.?12:-0.017
-0.422:-0.01l
-0.404:-0.027
-C.404:-3.029
-0.384:-0.033
-0.265:-0.010
-0.263:-0.042
-C.250:-0.040
-0.404:-0.032
-0.410:-0.0.?9
-0.236:-O.C36
-u.67l:-0.012
-O.o58:-0.011-0.252:-0.041
-0.460:-0.017
-0.967:-0.078
-1.070:-O.OO6
-0.045:-0.011
-0.365:-0.01d
-0.44fl:-0.045
-0. 4h9:-0.028
-0.61ls-0.045
-0.604.--O.U2
-0.070: 0.341
-0.609:-0.037
-0.420:-0.018
-0.39ls-0.034
-0.6tl:-0.079
-0.531:-0.010
-0.254:-0.032
-0.40fl:-0.177
-0.397:-0.3?l
O.C02: 0.8S5
-0. 348:-0.243
-0.336: -0.094
-0.390: -0.374
-0.385:-0.027
-0.377:-0.373
-0.013:-0.013
-0.033:-0.005-0.009:-0.009
-0.071i-0.070-O.C74:-0.071
-0.097:-0.069
-0.209:-0.014-0.22is-0.026
-0.586S-0.079
-1.077:-O.IU
-0.720: 0.230
-l.070i-0.112-C.440: 0.440
-1.075:-0.114
BURNOUT UJ4LITY
RANGE
-0.166: 0.049
-0.106: 0.055
-0.077: 0.087
-0.071: 0.427
-0.174S 0.255
-0.479: 0.002
-0.218: 0.2SO
-0.005: 0.405
-0.361: 0.261
O.lll: 0.428
0.286: 0.521
0.337: 0.533
0.335: 0.548
0.313: 0.542
0.345: 0.581
0.358: 0.576
0.395: 0.579
0.383: 0.592
0.303: 0.599
0.400: 0.580
0.401: 0.602
0.559: 0.576
0.496: 0.578
0.503: 0.633
0.030: 0.232
-0.003: 0.5170.026: 0.377
0.203: 0.567
0.109: 0.611
0.126: 0.5650.224: 3.350
-0.031: 0.254
-0.05o: 0.743
0.182: 0.019
0.196: 0.628
0.170: 0.469
0.125: 0.441
-0.028: 0.229
0.316: 0.257
0.119: 0.4130.066: 0.309
0.0)3: 0.408
-0.008: 0.325
0.381: 0.614
0.016: 0.591
0.230: 0.298
-0.011: 0.310
-0.169: 0.698
0.362: 0.844
O.lll: 0.610
0.159: 0.609
-0.279: 0.112
-0.218: 0.168
-0.268: 0.170
0.369: 0.359
0.099: 0.498
0.1C7: 0.50U
0.248: 0.494
0.269: 0.511
-0.337: 0.098
3.194: 0.662
0.276: 0.731
0.132: 0.224
0.177: 0.209
0.187: 0.910
0.028: 0.181
-0.118: 0.631
-0.177:-0.029
-0.287: 0.059
-0.147:-0.07l
0.188: 0.168
0.148: 0.403
0.329: 0.329
0.090: 0.091
0.092: 0.156
0.035: 0.124
-0.046: 3.107
-0.047: 0.159
-0.058: 0.189
-0.464: 0.658
-0.186: 0.530
-0.47o: 0.290
0.026: 0.640
-0.12U 0.634
TURNOUT HEAT
FLUX RANGE
_H/SflCH205.3: 310.3
193.4: 293.5
198.2: 314.2
96.3: 213.3
102.7: 267.0
127.4: 305. 4
106.7: 237.8
138.7: 178.0
28.0: 294.5
94.3: 299.3
90.5: 162.1
104.4: 159.8
104.4: 158.5
103.1: 160.9
96.4: 159.2
134.1: 156.9
132.8: 159.2
99.6: 158.5
102.8: 160.3
135.3: 15W.5
102. B: 160.5
133.2: 104.9
134.2: 105.9
102.8: 104.9
62.7: 65.5
47.1: 115.5
66.0: 114.2
86.1: 226.5
90.9: 204.2117.4: 215.7
101. 6: 146.5
01.6: 277.7
33.8: 246.5
8o.4: 245.7
90.2: 253.0
133.8: 254.3
155.5: 316.4
184.9: 312.3
159.3: 340.1
133.8: 218.3
120.4: 259.3
136.0: 259.6
106.3: 198.7
92.7: 277.9
89.0: 259.3
171.9: 222.4
164.9: 310.4
52.1: 214.5
i3.1: 103.1
91.2: 268.1
85.5: 258.7
44.8: 300.6
78.5! 364.0
93.4: 495.3
54.9: 155.5
36.4: 256.5
59.9: 161.5
114.5: 203.8
118.6: 171.9
92.1: 506.3
93.3: 258.3
22.6! 113.5221.5! 357.7
232.8! 278.2
7.6! 184.9
181.7: 352.1
78.3: 159.7
164.$: 223.9
190.4: 284.S
164.5: 165.4
133.7: 133.7
80.5: 273.9
111.7: 111.7
161.0: 161.7
143.7: 173.7
155.8: 193.8
201.3: 401.3
194.0: 343.0
57. 0: 133.8
9.8: 101.7
87.0: 398.0
15.9: 76.1
85.0: 226.0
14.7: 114.5
54
TABLE 2A (CONTINUED)
MAIN CHARACTERISTICS OF TEST ASSEMBLIES
ASS. DATA
SRCE
REF.
165 54
166 52
167 54
168 56
169 55
170 56
171 55
172 56
173 55
174 56
175 57
176 58
177 59
178 59
179 59
180 59
181 60
182 61
183 61
184 60
185 62
186 62
187 62
188 60
189 60
190 60
191 60
192 60
193 60
194 63
200 65
201 65
202 65
203 65
204 65
205 65
206 66
207 66
208 66
209 66
210 66211 66
212 67
213 68
214 68
215 68
216 69
217 69
218 70
219 71
220 71
221 72
222 72
223 72
224 72
225 72
226 73
227 73
228 73
229 74
230 74
231 74
232 74
233 74
234 74
235 74
236 72
237 75
238 76
239 76
240 76
241 76
242 76
243 76
244 76
245 76
246 76
247 76
248 76
249 77
250 77
251 77
252 77
253 77
SPECIAL NO.
FEATRS OF
RODS
7*?
X*
x?
+?<??
N
*#
?*m
?<
?7
7
7
*7$C
?7*C
?7tC
*7*C
?7tC
*7*C
*7tC
*<
?#+4
*
*
*
M
M
X?*-i<Sx*>-
x*>-<
M>->tf
**>
??x?
X*?*??>
**$-.>
*a*
X
X
Xt
*?
?
X
X
X?
X*??
?*
??
??<>*?>
?*>?*>
*?>
+<>??*>
*4
X*
X*
X*x?*
XX*
19.
20.
19.
21.
19.
21.
19.
19.
19.
19.
16.
37.
25.
25.
25.
25.
7.
7.
7.
7.
19.
19.
19.
7.
7.
7.
7.
7.
7.
19.
16.
10.
16.
16.
10.
16.
19.
19.
19.
19.
19.
19.
24.
29.
29.
29.
25.
25.
9.
7.
7.
1.
1.
1.
1.
1.
3.
3.
3.
4.
4.
4.
4.
3.
3.
3.
1.
3.
16.
16.
16.
16.
16.
16.
16.
16.
16.
9.
9.
3.
3.
3.
3.
3.
ROD
CIAM.
MM
19.9719. CS
19.57
10.7219.97
10.7219.57
10.7219.57
10.7215.06
13.80
10.7210.72
10.7210.72
12.70
17.5617.56
12.7020. CO
20.03
20.0012.70
12.70
12.7012.70
12.7017.70
20. CO15.00
15.0015.00
15.0015.00
15.0315.24
15.2415.24
15.24
1S..24
15.24
14.507.65
7.657.65
10.7710.69
10.49
9.109.10
10. CO
10.0010.00
10.0010.00
10. CO10.00
10. CO10.00
10. CO10.C3
10. CO10.00
10. CO
10.0010. CO
7.54
10.7210.72
10.7210.72
10.72
10.7210.72
10.7210.72
12.7012.70
9.0010.00
10.0010.00
10.00
ROD ROC HEATED LENGTH hEATO/ FlOW HVO'C
GAP PITCH LENGTH /HEATO WETTED AREA EOUIV.
/01AM. EO.DIA PERIH. OUM.
MM MM <LO-MM V*
1.53 1.C77
0.38 1.020
1.50 1.075
3.40 1.318
1.5C 1.0753.40 1.318
l.SC 1.075
4.42 1.412
1.5C 1.075
4.42 1.412
4.24 1.2827.60 1.565
3.38 1.315
3.38 1.315
3.3d 1.315
3.38 1.315
1.59 1.125
1.38 1.077
1.38 1.077
1.55 1.125
1.50 1.075
1.4G 1.070
1.50 1.075
1.59 1.125
1.55 1.125
1.59 1.125
1.59 1.125
1.55 1.125
1.59 1.125
15.30 1.765
4.50 1.300
4.SC 1.300
4.50 1.300
4.50 1.300
4.50 1.300
4.SC 1.300
1.27 1.083
1.27 1.083
1.27 1.081
1.27 1.083
1.27 1.983
1.27 1.083
1.52 1.105
1.7C 1.223
1.70 1.22)
1.70 1.223
3.53 1.328
3.43 1.321
1.4C 1.133
3.50 1.365
3.5C 1.385
-O.OC -0.000
-0.00 -0.000
-0.00 -0.000
-O.OC -3.000
-O.CO -0.000
1.75 U17S
1.7* 1.175
1.73 1.175
1.75 1.175
1.75 1.175
2.50 1.250
4.00 1.400
1.75 1.175
2.50 1.250
4.0C 1.400
-0.00 -0.000
4.76 1.600
3.38 1.315
3.38 1.315
3.38 J.315
3.38 1.315
3.38 1.315
3.38 1.315
3.38 1.315
3.38 1.315
3.38 1.315
4.01 1.316
4.01 1.316
3.20 1.356
4.30 1.430
4.3C 1.430
4.30 1.430
4.3C 1.430
3000.
2386.
3000.
1524.
3000.1524.
30">0.
1524.
3000.1524.
2700.4365.
2134.
2134.
2134.
2134.
255.
1635.
1615.
295.
3816.
3816.
3816.
295.
295.
295.
295.
295.
295.
6000.
3660.
3660.3660.
3660.
3660.
3660.
489.
489.
489.
469.
489.
489.
2134.
2419.
2419.
2419.
1676.
1829.
235.
2500.
1750.
200.
200.
200.
100.
290.
300.
600.
900.
300.
300.
300.
300.
300.
300.
300.
200.
1270.
2438.
2438.
2438.
2438.
2438.
2438.
2438.
2438.
2436.
4267.
4267.
400.
200.
420.
200.
400.
309.3
7*1.0
309.3
94. S309.3
116.4
30V.3
87. V
139.3
118.7
145.9
119.3
140.0
128.7
129.1
134.0
39.2161.7
159.7
50.0
396.5
396.5
408.6
50.6
50.6
50.6
50.6
50.6
50.6
621.6
195.7
195.7
195.7
195.7195.7
195.756.9
58.9
56.9
58.9
58.9
56.9
245.4
413.3
413.3
413.3104.4
114.3
31.1
196.0
137.6
20.9
4.5
20.9
2.3
6.6
20.7
41.4
62.2
23.7
23.7
17.9
11.7
20.7
15.9
10.4
4.5
66.0
145.9
145.9
145.9
145.9
145.9
145.9
145.9
145.9
145.9
197.7
197.7
24.7
9.2
19.4
15.9
31.9
0.761
0.737
0.781
0.714
0.701
0.747
0.781
0.720
0.781
0.76-.
0.712
0.735
C.740
0.708
0.7020.736
0.6450.679
0.679
0.834
0.782
0.782
0.754
0.834
0.834
0.634
0.834
0.834
0.834
0.782
0.712
0.712
0.712
0.712
0.712
0.712
0.778
0.778
0.778
C.776
0.778
0.778
0.760
0.793
0.793
0.793
3.636
C.603
0.677
0.619
0.619
1.000
0.217
l.OOO
0.217
0.217
0.525
0.525
0.525
0.570
0.570
0.5590.514
0.525
0.505
0.466
0.217
0.473
0.6890.689
0.689
0.689
3.689
0.689
0.689
0.689
0.689
0.618
0.618
0.460
0.448
0.448
0.488
0.486
2890.
551.
2690.
2643.
2890.2734.
2890.
2772.
2890.
256b.
3502.
14282.3194.
3350.
3339.
3350.
526.999.
999.
526.
2672.
2872.
2788.526.
526.
526.
526.
526.
526.
2681.
3525.
3525.
3525.
J525.
3525.
3525.
1886.
1886.
1886.
1880.
1886.
1686.
2283.
1019.
1019.
1019.
2987.
2821.561.
636.
636.
346.
346.
346.
346.
346.
341.
341.
341.
397.
397.
526.
608.
341.
443.
678.
346.
360.2251.
2251.
2251.
2251.
2251.
2251.
2251.
2251.
2251.
1937.
1937.
344.
511.
511.
296.
296.
7. id2.44
7.58
11.43
7.58
9.77
7.58
12.47
7.58
9.81
13.10
26.89
11.24
11.74
11.60
11.74
4.B6
6.87
6.87
4.86
7.52
7.52
7.04
4.86
4.86
4.66
4.86
4.86
4.86
7.54
13.31
13.31
13.31
13.31
13.31
13.31
6.45
6.45
6.45
6.45
6.45
6.45
6.61
4.64
4.64
4.64
10.219.64
5.12
7.88
7.88
9.56
9.56
9.56
9.56
9.56
7.61
7.61
7.61
7.22
7.22
9.21
13.22
7.61
9.50
13.46
9.50
9.10
11.51
11.51
11.51
11.51
11.51
ll.il11.51
11.51
11.5113.34
13.34
7.46
9.71
9.71
6.12
6.12
HEATED"
EJUIV.
9.73
9^73
16.09
9.70
13.09
9.70
17.33
9.70
12.84
18.50
36.60
15.18
16.58
16.53
15.92
7.54
10.11
10.11
5.83
9.62
9.62
9.34
5.83
5.83
5.83
5.83
5.83
5.83
9.65
18.70
18.70
16.70
18.70
16.70
18.70
8.29
8.29
6.29
8.29
8.29
8.29
8.69
5.85
5.85
5.85
16.05
15.99
7.56
12.72
12.72
9.5o
44.03
9.56
44.03
44.03
14.48
14.48
14.48
12.65
12.65
16.73
25.72
14.48IB. 81
28.76
44.03
19.25
16.71
10.71
16.71
16.71
10.71
16.7116.71
16.71
16.71
21.58
21.58
16.21
21.68
21.68
12.55
12.55
RADIALFORM
FACTOR
1.333
1.930
1.512
1.087
1.105
1.246
1.105
1.097
1.099
1.341
1.000
1.183
1.009
1.118
1.098
1.122
1.300
1.300
1.000
1.2221.141
1.141
1.141
1.181
1.157
1.122
1.096
1.081
1.386
1.128
1.037
1.203
1.203
1.196
1.197
1.263
1.086
1.086
1.066
1.066
1.0661.086
1.286
1.568
1.638
1.736
1.085
1.093
1.000
1.000
1.000
2.638
1.000
2.599
1.000
1.090
1.000
1.000
1.000
1.030
1.000
1.030
1.000
1.000
1.000
1.033
1.300
1.000
1.047
1.047
1.047
1.145
1.146
1.146
1.146
1.159
1.157
1.000
1.000
1.000
1.090
1.000
1.030
1.000
AXIAL
FORM
FACTOR
1.003
1.000
1.003
1.000
1.000
1.000
l.OOO
1.000
1.000
1.000
1.444
1.003
1.000
1.000
1.030
1.000
1.000
1.003
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.300
1.000
1.000
l.OOO
1.000
1.000
1.300
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.4522.258
2.315
2.257
1.0001.000
1.0001.000
1.9001.419
1.0001.379
1.0001.000
1.0001.000
1.0001.000
1.0001.000
1.000
1.0001.000
1.0001.000
1.0001.563
1.5631.563
1.8561.856
1.8561.856
1.8561.856
1.691
1.6721.000
1.000
1.0001.000
1.000
NO. GR 13
OF TYPE
GRIDS
5.
23.
5.
4.
5.4.
5.
4.
5.
4.
6.
7.to.
10.
10.
10.
1.
3.
3.
1.
S.
42.
9.
1.
1.
1.
1.
1.
1.
12.
7.
7.
7.
7.
7.
7.
7.
8.
10.
12.
7.
12.
4.
7.
7.
7.
2.
4.
0.
10.
7.
0.
1.
1.
4.
4.
1.
3.
5.
0.
1.
0.
3.
0.
0.
0.
0.4.
9.
8.9.
9.
9.
9.
9.
9.
9.
17.
16.
2.
2.
3.
2.
2.
6.1
3.5 A6.1
7.C
6.1
2.0
13. C
7.C
13.0
2.C
5.1
7.0
10.0 4
10. C 4
10. C A
10. 0 4
3.2
7.C
6.2
3.27.0
6.2 A
7.C
3.2
3.2
3.2
3.2
3.2
3.2
7.C
10.0
10.0
10.0
10.0
10.0
10.0
3.3 A
3.3
3.3
3.3
3.2
3.3
8.3
8.3
8.3
8.3
11.0
11.0
O.C
12.0
12.0
0.0
15.1
15.1
15.2 A
15.1 A
4.2
4.3
4.3
0.0
4.3
0.0
0.0
0.0
0.0
0.0
0.0
3.4
11. C A
11.3 A
11.6 A
11. C A
10.2 A
10.2
10.1
11.4 A
11.4
11. C A
11.3 A
16.C
16.0
16.0
4.3
4.3
55
TABLE 28 (CONTINUED)
NUMBER AND RANGE OF BURNOUT TESTS WITH EACH ASSEMBLY
ASS.
~16S
166
167
16S
16J
170
171
17.4
174
175
176
177
17d
179
180lai
162
163
184
18*
186
167Ida
U9
190
191
192
4-3
194
200
201
202
203
204
2C5
206
207
20d
20)
210
211
212
213
214
215
216
217
2 It!
219
220
221
222
223
224
225
226
227
228
229
230
231
232
233
234
235
236
237
238
239
240
241
242
243
244
245
246
247
24d
249
250
251
252
253
NO.
CFTESTS
~^a~
51.
6J.
11.
116.
11.
185.
*
106.
9.
43.
10.
11.
32.
42.
4.
3?C.
70.
147.
7.
262.
102.
22..).
29.
8.
12.
7.
10.
29.
40.
33.
26.
20.
27.
22.
23.
U.
10.
7.
15.
9.
5.
1.
4.
1.
59.
54.
2.
9.
92.
60.
59.
27.
10.
1.
53.
29.
41.
26.
21.
36.
4.
28.
33.
13.
43.
4.a.
32.
36.
29.
23.
17.
35.
18.
30.
33.
14.
10.
13.
19.
6.
10.
MESSOP?
SEA
3.C>9: o.lvi
?.2?4:l.<.7sO
5.C3U 6.100
10. 3*2 : 13. 3*2
l.CnS: S.ciirt
10.342MO.J4?
?..^j: S.247
10.3*2: 10.242
6.727: 6.V62
4.S70: 6.-JSO
I?. 507:13. 8a<>
11. 128:15. V>-?
11. 12il:l5.Sb4
12.507:1 }.8Sf.
O.C4U Cl.jW
J.C5J* 5. .'37
?.-iol: 6.109
O.C99: O.C'V-J
7.S11: ?.109
4.C9'i: ?i.67d
4.6 7t' Ji? }54
0.100: 0.1CO
O.C96: 0.100
O.C99: G.C-J9
O.C99: O.C99
O.C99: 0.099
O.C99: C.C99
5.COU 6.355
6.660: 7.200
6. 650: 7.020
6.360: 7.G30
6.930: 7.C50
6.690: 7.300
6. ?0: 7.000
1.551: 3.551
3.55U 3.551
3.55l> 3.551
3.551: 4.137
3.55U 3.551
3. 551: 3.551
13.790:13.790
13.790:1:1.740
13. 790: I 3. 790
13.790:13.7*0
11.9a2:l6.203
10.170:15.686
11.790:13.790
12.300:12.400
12,200:13.900
9.800:13.700
9.600:13.700
9.800:13.700
9.800: 9.800
9.80C: 9.800
C.74CS 1.670
1.030: 4.220
0.590: 4.170
0.680: 1.960
O.SdO: 1.620
0.690: 1.370
0.980: 1.570
C.SdO: 1.230
0.780: 1.620
0.910: 1.570
9.800:13.700
6.695: 6.895
10.280:14.513
10.273:16.768
10.225:16.644
10.363:16.616
10.287:14.810
10.328:14.541
10.32U17.030
10.280:16.547
10.32U16.747
10.342:16.527
12.355:16.720
10.300:10.300
9.800: 9.800
4.900: 4.800
9.600: 9.800
9.00C: 9.800
"ASS f-LUX
16.40: 1*8.02
-14.45: *?CS. S3
JA.C5: 377.34
1 .' rt . ? * : i/3.96
Is. SB: ;-|B.32
li-i.^J: 410.94
IS. 73: 202.72
IS. 71: 295.12
Hi.tJ: 272.60
69.40: ib2.t>0
36.13: <)2.20
70. 0?: -.00.09
VC.oD: tV-.ZZ
7e.c4: J72.o9
74. d9: <.?,?. 33
1,2': !i.i3
5 7, 72: ?34. 74
3h.CS: ."id.ao
3.37: 5.2,1
IB. 54: 291. <!9
IS. 87: 302. 74
35. 31: 2'.9.42
;.43: 5.30
1.71: o.ll
2.56: 5.2'l
1.82: 7.6d
;.??/: 7.27
2.2o: 7.26
S.<>4: 363.72
11.22: 200.25
10. ?S: 704.56
12.05: 203.60
11.82: .'00.52
11.17s 203.25
11.83: 200.87
70.25: 1S6.6S
69.57: 19o. 11
69.85: 195.43
66.18: 201.40
69.57: 194.62
69.98: 196.11
67.00: 116.03
135.49: 135.49
204.25: 4C6.19
399.82: 3V9.82
131.55: 372.96
138.34: 371.61
54.66: 134. Hi
7C3.80: 253.70
150.00: 305.00
39.00: 223.00
28.00: 331.UO
29.30: 231.70
69.30: 87.30
234.00: 234.00
67.20: 277.80
101.90: 273.10
65.80: 271.90
49.10: 26o.oO
96.00: 267.80
44.60: 252.40
90.90: 92.00
90.40: 271.80
90.90: 270.10
105.90: 177.50
29.40: 334.00
33.91: 135.62
280.74: 492.31
273.96: 449.09
203.43: 486.89
259.04: 490.96
203.43: 490.96
212.93: 495.02
279.38: 535.71
345.64: 501.80
272.60: 490.96
271.25: 465.53
340.41: 503.16
76.80: 434.40
29.60: 432.50
30.00: 443.00
31.10: 222.40
30.30: 235.80
INLET dUALlTV
-0.226:-0.313
-1.072:-0.125
? 0.225:-3?026
-0.26U-J.130
-0.212:-0.009
-0.2o5:-0.127
-0.2C3:-0.014
-0.206: 0.24-*
-0.263:-0.134
-0.220:-0.009
-3.052:-O.OOV
-0.448:-0.160
-0.51d:-O.OB9
-C.749:-0.131
-2.275:-0.197
-0.070: D.DC'6
-0.240: 0.41'?
-0.257: 0.42;
-J.018:-0.01o
-0.198: 0.277
-u.t'02,: 0.4O9
-0.2CU-0.026
-C.019:-0.014
-0.057:-0.014
-0.01d:-0.016
-0.060:-0.052
-0.059:-0.057
-0.060:-0.058
-0. 190:-0.0?'3
-0.539:-O.T?5
-0.528:-0.?'*0
-0.-.28:-0.0'.9
-0.3S5:-0.052
-0.508:-0.043
-0.402:-0.057
0.325: 0.683
0.351: 0.6dl
0.439: 0.673
0.3^1: 0.682
0.486: 0.607
0.482: 0.610
-0.343:-0.179
-0.353:-0.3S3
-0. 349:-0.339
-0. 138:-0.138
-0. 766:-0.094
-0.683:-0.092
-0.257:-0.039
-0.512:-0.324
-0. 754:-0.145
-O.dl6: 0.011
-0.727: 0.015
-0.d2U 0.006
-0.432:-0.016
-0. 178:-0.178
-0.105: 0.237
-0. 158:-0.064
-0. 162:-0.0al
-0. 100: 0.212
-0.074: 0.217
-0.059: 0.224
-0.015: 0.079
-0.044: 0.290
-0.006: 0.279
-0.015: 0.111
-0.692:-0.002
0.256: 0.517
-0.314:-0.073
-0.565:-0.094
-0.526:-0.089-0.433:-0.092
-0.457:-0.079
-0.449:-0.107
-0.610:-0.116
-0. 334!-0.081
-0.533:-0.087
-0.537:-0.121
-0.40U-0.104
-0.609:-O.OS1
-0.835: 0.180
-0.876: 0.300
-0.43o:-0.020
-0.902:-0.011
BURNOUT OUALITV
RANGE
0.264: 0.302
0.129: O.SH4
0.100: 0.649
-0.306: 0.191
0.257: 0.840
-0.044: 0.132
0.279: 0.8?0
?.rt fl*i"A* A 1 ***iU* Uv J? U* 1 ?> '
0.1V6: 0.797
-0.024: 0.1V6
0.272: 0.609
0.311: 0.514
0.075: 0.3oO
0.033: 0.366
-0.023: 0.145
O.U64: 0.2BS
0. ?64: 0.91S
O./aO: 0,632
0.177: 0.645
C.4dO: 0.600
0.255: 0.960
0.2V2: O.d64
0.245: O.dOl
0.482: 0.663
0.420: 0.004
0.501: 0.676o.46i: o.aoi
0.49&: 0.706
0.525: 0.865
0. J42: C.9V9
0.150: 0.955
0.050: 0.916
0.102: 0.841
0.112: 0.984
0. 110: 0.822
0.129: 0.807
0.373: 0.724
0.431: 0.743
0.508: 0.747
0.446: 0.775
0.507: 0.669
0.509: 0.691
0.012: 0.283
-0.078:-0.078
-0.130:-0.108
-0.000:-0.000
-0.140: 0.102
-0.173: 0.102
0.177: 0.266
0.110: 0.1 ?0
-0.003: 0.147
-0.418: 0.282
-0.414: 0.132
-0.398: 0.286
-0.402: O.'Ul
-0.136:-0. .36
-0.023: 0.310
0.019: 0.129
0.035: 0.276
-0.008: 0.374
0.063: 0.314
0.073: 0.336
0.091: 0.165
0.063: 0.340
0.061: 0.326
0.055: 0.168
-0.462: 0.125
0.345: 0.710
-0.063: 0.059
-0.159: 0.038
-0.200: 0.050
-0.146: 0.024
-0.146: 0.050
-0,149: 0.026
-0.266: 0.045
-0.114: 0.028
-0.211: 0.039
-0.043: 0.095
-0.088: 0.090
-0.209: 0.126
-0.352: 0.273
-0.323: 0.480
-0.174: 0.307-0.232: 0.243
BURNOUT HEAT
FLUX RANGE
20.9: 89.2
12.5: 94.0
52.2: 209. t
152.1: 256.2
23.8: 138.2
117.7: 219.6
19.2: 121.9i ft i s * ?ftn &
LO I ? 3 ? cOU**t
20.1: 124.2
153. M: 236.3
d3.1: 143.2
80.8: lll.l
75.7: 201.9
76.0: 224.8
117. o: 231.3
94.6: 175.2
16.9; 52.6
40.9: 153.2
50.6: 252.6
25.5: 35.7
14.8: 120.7
13.9.- 115.5
36.6: 116.3
21.2: 35.7
17.4: 51.5
21.2: 35.2
16.6: 51.8
25.5: 50.9
22.).: 52.4
6.6: 115.0
21.5: 242.7
23.2: 262.2
26.4: 228.6
26.9: 222.5
24.6: 212.5
27.0: 196.4
16.4: 76.1
31.9: 92.8
33.9: 81.9
SO. a: 102.1
22.9: 49.4
23.8: 57.9
15.1: 22.8
97.3: 97.3
121.4: 209.3
138.4: 138.4
128.9: 299.1
170.4: 340.4
249.8: 253.3
165.0: 191.0
144.0: 263.0
214.0: 710.0
248.0: 884.0
238.0: 664.0
466.0: 790.0
490.0: 490.0
157.2: 485.0
260. 5: 428.0
172. U 346.6
170.1: 506.7
197.9: 456.9
141. U 487.1
324.7: 412.6
95.8: 505.6
136.1: 465.1
281.0: 506.7
233.0: 780.0
37.5: 69.1
230.7: 356.1
155.4: 327.7
240.1: 396.7
113.4: 421.4
187.2: 309.7
187.9: 355.4
82.8: 279.3
264.1: 428.7
196.6: 452.8170.5: 318.0
219.0: 316.6
263.0: 475.0
210.0: 640.0
93.0: 698.0
221.0: 668.0
198.0: 430.0
56
TABLE 2A (CONTINUED)
MAIN CHARACTERISTICS OF TEST ASSEMBLIES
ASS. DATA
SRCE
REF.
254
255
256
257
258
259
260
261
262
263
264
265
266
267
268
269
270
271
272
273
274
275
276
277
278
279
280
281
282
283
284
285
286
287
288
289
289
290
290
291
291
292
293
294
295
296
297
298
Al
A2
A3
A4
AS
A6
A6
A6
A7
A7
A7
A8
A9
AID
All
A12
A13
A14
A15
A16
A17
A18
A18Aia
A19
A19
A20
A21
A22
A23
A24
77
77
77
77
77
77
77
77
77
77
77
78
78
78
78
78
78
78
78
78
7?
78
78
78
78
78
79ao
81
82
62
82
82
62
82
45
45
45
45
46
46
83
33
25
91
18
18
42
84
84
84
84
84
85
85
85
65
65
85
86
86
86
86
86
86
86
86
86
86
87
87
87
87
87
88
89
89
89
90
SPECIAL NO.FEATRS OF
RODS
X*
X*x?*
x??x??
X**
X4*
M*Y
X??Y
X??Y
X??Y
X*x?a
x?a
X*x<
x?ax?
X*x?
x?x?
x?<->
X*xia
?*
?*lx?a
x*sx?
x*:x?
x?;
**L
*?L
+VL
**L
?*L
*?L?
*?0?E
**!<
M
H
N
<
>
>
>
>
V
V
V
V
DV
OVV
OV
Vov
"<
"<
"<??
N
*
3.
3.
3.
3.
3.
3.
3.
3.
3.3.
3.20.
20.
20.
20.
20.
20.
20.
20.
20.
20.
20.
20.
20.
20.
1.1.
25.
20.
20.
20.
20.
20.
20.
9.
9.
9.
9.
16.
16.
1.
9.
1.
5.
19.
19.
19.
1.
1.1.
1.1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.
1.1.
1.
1.
1.
1.
1.
1.1.
ROC ROD BOO hEATED LENGTH fEATC/
OIAH. GAP PITCH LENGTH /H=ATO nETTFO
/01AM. SJ.01A PERl?.
Mf^ MM
10. CO 4.3C 1.430
10.00 4.30 1.-.30
10.00 2.30 1.230
10.00 2.30 1.230
10.00 0.10 1.010
10.CO 0.10 1.010
10. CO 0.4C l.CoO
10.00 4.30 1.430
10. CO 4.3C 1.43C
10. CO 4.30 1.430
10.00 4.30 1.4306.35 2.29 1.360
6.35 2.29 1.363
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 l.'oO
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
7.11 1.52 1.214
7.11 1.52 1.214
9.52 -O.CO -0.000
9.52 -O.CO -0.000
13.75 2.51 1.183
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
6.35 2.29 1.360
14.33 4.42 1.309
14.33 4.42 1.309
14.33 4.42 1.309
14.33 4.42 1.309
14.27 4.44 1.311
14.27 4.44 1.311
8.12 -0.00 -0.000
10.20 3.20 1.314
10.20 -O.CC -0.000
10.95 3.12 1.265
15.54 1.02 1.065
15.54 1.C2 1.065
14.33 1.68 1.131
15.87 -O.OC -0.000
15.87 -C.CC -0.000
15.87 -O.OC -0.000
15.87 -C.OC -0.000
15.87 -O.OC -0.000
13.12 -O.CC -O.OCO
13.72 -O.CC -0.000
13.72 -C.CC -? 0.000
13.72 -O.CC -0.000
13.72 -O.CC -0.000
13.72 -0.00 -0.000
12.70 -0.00 -0.000
19.05 -0.00 -0.000
53.97 -O.CO -0.000
25.40 -0.00 -0.000
12.70 -O.CC -0.000
19.05 -0.00 -0.000
19.05 -0.00 -0.000
19.05 -O.CO -0.000
19.05 -0.00 -0.000
19.CS -0.00 -0.000
15.19 -0.00 -0.000
15.19 -O.CC -0.000
15.19 -O.CC -0.000
15.19 -O.CO -0.000
15.19 -0.00 -0.000
12.70 -C.CC -0.000
14.98 -0.00 -0.000
10.21 -C.OO -0.000
10.21 -O.CO -0.000
15.42 -O.CO -0.000
,_UM_
420.
420.
200.
420.
100.
203.
200.
200.
230.
420.
420.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
1372.
914.
8230.
559.
1372.
137i.
1372.
1372.
1372.
1372.
1829.
1829.
1829.
1829.
3658.
3658.
711.
1183.
1183.
2774.
1930.
1930.
495.
457i,
3658.
3658.
3658.
3658.
274.3.
2743.
2743.2311.
2311.
2311.
610.610.
610.610.
610.
610.
610.
610.
610.
610.
488.
4b8.
468.
980.980.
6502.
3288.
1191.
795.
1829.
"~2379~
23.915.V
33.5
8.0
15.915.9
15.S
15.9
33.5
33.5
152.8
152.6
152.8
152.8
152. d
152. t?
152.6
152.4
175.6
152.8
152.3
152.8
247.9
247.9
247.9
17.1
154.1
45.5152.8
152.8
152.8
152.6
152.8
152.896.4
96.496.4
96.4
195.9
19*>.9
39.280. a
66.1
162.9
256.4
256.4
46.9
387.9
310.3
310.3
310.3
310.3
423.0
123.0
123.0
103.7
103.7
103.7
23.3
32.3
33.S
32.0
23.3
32.3
32.3
32.3
32.332.3
35.5
35.5
3S.5
71.4
71.4
248.2
766.5
97.1
64.0161.4
0.?.64
O.H64
0.468
0.486
0.4S6
C.488
0.468
0.483
0.466
3.468
0.486
0.720
0.720
C.720
0.720
0.723
0,720
3.720
0.720
0.726
0.720
1.720
0.720
0.748
0.748
0.748
C.273
0.270
0.763
0.720
C.720
0.720
C.720
0.720
C.720
0.650
0.650
0.050
0.650
0.711
0.711
0.334
0.630
0.348
0.507
0.782
C.782
J. 767
0.431
0.431
0.431
C.431
0.431
0.382
0.382
0.382
0.382
0.382
0.382
C.364
0.415
0.464
0.430
0.364
0.415
0.415
0.415
0.415
0.415
0.423
0.420
C.420
0.420
0.423
0.364
0.469
0.403
0.4031.000
I- LOw
52*iMl_
414.
4l4.
246.
2"?0.
296.
296.
290.
29o.
29o.
29o.
29o.aso.
890.
6Sb.
840.
696.
??><>.
89o.
896.
77V.
896.
89o.
896.
616.
618.
618.
400.
400.
3314.
696.
696.
896.
896.
896.
896.1921.
1921.
1921.
1921.
3348.
3348.
116.
1056.143.
732.1746.
1746.
2258.
147.
147.
147.
147.
147.
240.
240.
240.
240.
240.
240.261.
262.
771.
380.
261.
282.
282.
282.
2S2.
282.
164.
164.
164.
164.
164.
261.
50.
98.
98.375.
HYO'C
EOulV.
D1A-.
JJJS. .
8.14
6.14
6.12
6.12
s.li
6.12
6.12
6.12
6.12
6.12
6.12
6.46
0.46
6.*6
6.46
6.46
0.46
6.46
6.46
5.67
6.46
6.46
6.46
4.14
4.14
4.14
14.44
14.44
9.37
6.46
6.46
6.46
6.40
6.46
6.4612.34
12.3412.34
12.34
13.27
13.27
6.05
9.23
6.23
8.63
5.86
5.o8
8.10
5.08
5.08
5.08
5.06
5.088.S.I
8.51
8.51
8.51
8.51
8.51
9.53
7.82
8.43
8.20
9.53
7.82
7.82
7.82
7.82
7.82
5.77
5.77
5.77
5.77
5.77
9.53
2.014.94
4.94
11.33
t'.UI..
OIAM.?3?
17.57
17.57
12.55
12.55
12.55
12.55
12.55
12.55
12.55
12.55
12.5S
0.98
6.98
a. 96
8.98
0.96
8.96
8.98
8.98
7.61
3.99
8.98
6.96
5.53
5.53
5.53
53.42
53.42
12.27
4.98
6.98
0.96
6.96
6.98
8.98
16.97
16.9718.97
18.97
18.6718.67
18.14
14.64
17.89
17.03
7.53
7.5310.56
11.79
11.79
11.79
11.79
11.79
22.30
22.30
22.30
22.30
22.30
22.30
26.20
18.85
18.18
19.06
26.20
18.85
18.85
18.85
16.85
18.85
13.72
13.72
13.72
13.72
13.72
26.20
4.29
12.27
12.27
11.33
RACIAL
FORM
FACTOH
~77030~"
l.?00
1.330
l.OUO
1.333
1.330
1 .0 00
1.0331.000
1.000
1.033
1.530
1.533
1.530
1.533
1.033
1.330
1.333
1.500
1.533
1.000
I. 000
1.329
1.030
1.030
1.107
1.000
1.000
1.680
1.000
1.000
1.033
1.030
1.000
1.000
1.000
1.000
1.033
1.000
1.000
1.000
1.000
1.0001.030
1.000
1.077
1.077
1.069
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.0001.001
AXIAL
FACTOR
"ITooo"
1.000
1.000
1.000
I. 000
1.000
1.330
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.3031.000
1.000
1.000
1.000
1.0301.347
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.330
1.000
1.367
1.387
1.000
1.000
1.0003.139
1.000
1.300
1.000
1.000
1.000
1.446
1.160
1.744
1.39$
1.432
l.*,46
1.320
1.347
1.356
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.000
1.460
1.4601.460
1.344
1.344
1.000
1.000
1.000
1.0001.260
NO. GRID
OF TYPE
GRIDS
3.
3.
2.
3.
2.
3.
3.
3.
3.
3.
3.5.
6.
5.
4.
6.
5.
4.
4.
4.
4.
4.
4.
4.5.
5.
3.
-0.
2.
4.
4.
4.
4.
4.
4.
3.
3.4.
3.
8.
8.
0.
5.
7.
22.
7.
31.
2.
13.
10.
10.
10.
1C.
9.
9.
9.
5.
5.
5.
2.
6.
6.
6.
2.
6.
6.
6.
6.
6.
2.
2.
2.
4.
4.
28.
8.
2.
2.4.
4.3
4.3 4
16.0
16.0
16.0
16.0
16. C
16. C
16. C
16.0
16.C
17.1
17.1 A
17.2
17.2
17.2 a
17.2
17.2
8.2
8.2
6.2
8.1
17.2
8.3
8.3
8.3
3.1
-0.0
10.0
8.2
8.2
10.110.1
17.2 a
17.2 a
10.0
10.0
10. C
10.0
10.0
10.0
0.0
5.C
3.1
3.4
3.2
3.2 i
3.2
4.1
4.
4.
4.
4.
? 3. 1
3. *
3. <
3.
3.
3. '
3.3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.
3.1
57
TABLE 28 (CONTINUED)
NUMBER AND RANGE OF BURNOUT TESTS WITH EACH ASSEMBLY
ASS.
2J>4
255
256
257
253
259
260
261
262
263
264
265260
267
268
264
270
271
272
27J
274
275
276
277
278
274
280281
282
283
284
285
286
287
2?8
2t?4
284
290
290291
291
292
293294
295
296
297
298
Al
A2
A3
A4
A5
A6Ao
A6
A7
A7
A7
A8
A9
A 10
All
A12
A13
A14
A15
A 16
A17
A18
AU
AJL8
A19
A19
A20
A21
A22A2J
A24
NO.
OFTESTS
6.
B.
2.9.
5.
2.
5.
9.
4.
16.a.
34.
32.
42.
36.
5.
30.
40.
SO.
54.
25.
33.
32.
45.
54.
15.
19.
4.
21.
6.
5.
40.
15.
16.
15.
35.
35.
23.
24.
40.
43.
57.ia.
2.
S.
5.
5.
37.
19.
308.
156.
50.
23.
1.
19.
5.
5.
6.
12.
246.
16.
22.
4.
37.
7.
57.
5.
4.
6.
18.
6.
5.
10.
11.
21.
71.
i3.
39.
48.
PRESSURE
RANGE
., , ,. , ftfA - ,
9.800: 9.800
4.SOO: 9.aiX>
9.800: 9.6JO
?.bOC: "..80.3
9.&30: 9.600
9.800: 9.800
9.600: 9.t>03
4.900: 9.600
4.SOC: 9.300
9.80C: s.803
9. 800: 9.BOO
8.274:13.710
8.274:13. 790
8.274:13.793
8.274:11.790
13. 790OJ. 793
fl.274U3.790
8.2/4:13.740
0.274:13.790
8.239:U.858
8.239:13.845
8.274:13.793
8.274:13.790
8.274:13.793
2.758U3.790
8.274:13.790
6.895: 6.895
6.895: 6.895
O.C94: 0.137
6.274: 8.274
8.274: 8.274
8.274:13.790
8.274:13.790
8.274U3.790
8.274:13.790
5.516: 6.895
5.516: e.895
5.516: 6.895
5.516: 6.8955.481: 6.964
5.392: 6.99810.411:15.996
12.940:13.78012.474:11.004
13.^00:13.907
6.895: 6.895
6. ?95: 6.d95
6.895: 8.274
6.722: 6.998
5.C68: 7.102
5.102: 7.C676.516: 6.998
6.688: 6.99a
6.845: e.895
6.895: 6.929
6. ?95: 6.895
6.833: 6.998
6.89$: 6.929
6.860: 6.964
0.222: 0.732
0.44&: 0.712
0.474: 0.6250.474S 0.563
0.397: 0.531
0.563: 0.722
0.477: 0.791
0.461: 0.590
0.44o: 0.446
0.450: 0.598
6.S15: 7.060
6.991: 7.074
6.915: 7.033
6.S5,'; 7.171
6.950: 7.115
6.895: 6.895
5.263: 8.280
6.983: 7.196
7.C01: 7.123
6.750:13.921
"?AiS KUX
RANGE
_-__?X??Sa?li37.40: ?30.30
82. aO: 233.30
56.83: 234.03
74.00: 470.00
99.00: 440.00
219.00: 220.40
74.00: 446.00
100.03: 235.00
72.00: 2C9.00
75.00: 447.00
76.00: 442.53
33. e3: 546.56
33.50: 542.49
33.77: 545.20
11. C&: ->43.d5
3'. 77: 135.04
33. ?3: 4VC.96
31.77: 4CJ.SB
33.50: 526.22
35. i;: 469.12
31. 4o: 271.65
33.53: 272.3*
33.o3: 4C6.7J
33. ti: 543.17
33.91: 406.23
6.75: 24.09
66.46: 135.62
36.62: 135.62
241.70: 629.70
67.40: 272.47
67.81: 2C9.94
33.50: 274.39
67. 81: 272.20
67.40: 271.42
67.95: 271.79
34.03: 136.75
32.90: 133.93
33.11: 136.92
33.38: 138.20
33.92: 137.82
33.30: 138. 82
66.32: 41C.67
47.90: 224.10
93.30: 94.00
190.55: 260.40
136.98: 4C9.58
139.69: 410.94
67.81: 271.25
131.42: 403.34
134.27: 339.46
134.54: 345.02
134.00: 339.60
134.54: 339.33
150.54: 150.54
112.57: 189.87
150.54: 189.87
188.52: 189.87
153.25: 154.61
112.57: 153.25
401.04:1365.72
437.79:1342.13
420.84:1328.16439.28: 882.09
500.45:1556.95
S60. 89:1463. 91
430.33:1335.89
161.26: 969.70
890.77: 914.32
492.72: 999.81
39.97: 97.30
52.72: 68.9448.89: 97.23
31.19: 104.24
39.14: 93.67
66.73: 201.54
78.27: 385.28
110.36: 381.99
110.10: 383.94
67.68: 342.31
INLET OUALITY
MANGE
-0.640:-0.024
-3.599:-0.002
-0. 39o:-3.25<?
-0.462: -0.020-0.3&2:-0.016
-0.233:-0.059
-0.41-?:-3.020
-0.553l-0.093
-0.26V:-0.002
-0.402: 0.603
-0.624: 0.253
-O.d56:-O.lia
-l.077:-0.127
- .068:-0.125- .C75:-0.1ia
- .637:-3.3<?7
- .J77:-0.118
- .C8U-0.114
- .C75:-3.103
- .C79:-0.125
- .072:-0.122
- .075:-0.122
- .064:-0.113
- .075:-0.11o
- .077:-0.063
-O.e><.2:-0.13a
0.300: 0.71J
-0. l?Q:-0.053
-C.160:-0.090-0. 325:-0.134
-0.318:-0.136
-1.083:-0.118
-3.402:-0.133
-0.640:-0.128-0.636:-0.131
-0.51l:-0.012
-O.S40:-0.012
-0.535:-0.012
-0.510:-0.013
-0.378: -0.032
-0.40&:-0.039
-C.497:-0.059
-0.704:-0.105
-0.212:-0.198
-0.348:-0.28o
0.024: 0.177
0.025: 0.171
-0.355: 0.323
-0.242:-0.008
-0.4C4:-0.034
-0.271:-0.034
-0. 23&: -0.028
-0.24b:-0.035
-0.056: -0.056
-0.462:-0.026
-0.47l:-0.018
-0. 335:-0.043
-0.372:-0.058
-0.413:-0.060
-0. 244.--0.081
-C.230:-0.119
-0.294:-0.122
-0.247:-0.133
-0.374:-0.210
-0. 317S-0.150-0.2aO:-0. 128
-0.32l:-0.193
-0.333:-0.159
-0.433:-0.236
0.309: 0./55
0.445: 0.756
0.433: 0.754
0.247: 0.745
C.360: 0.759
-0.563:-0.049
-0.300: 0.488-0.227: 0.515
-0.190: 0.522-0.417:-0.026
BURNOUT JUALITY
RANGE
-0.174: 0.209
-0.161: 0.233
-0.177:-0.15l
-0.179: 0.209
-0.328: O.OOB
-0.233:-0.03l-0.300: 0.371
-0.395: 0.005
-0.090: 0.132
-0.1 on: 0.709
-0.289: 0.311
-0.144: 0.512
-0.421: 0.515
-0.4S1: 0.500
-0.409: 0.484
3.348: 0.636
-0.331: 0.687
-0.440: 0.035
-0.3C4: 0.468
-0.3V7: 0.424
-0.017: 0.649
-0.339: 0.639
-0.168: 0.631
-0.173: 0.741
-0.024: 0.774
0.672: 0.958
0.333: 0.729
0.208: 0.502
-0.121:-0.068
0.159: 0.515
0.193: 0.449
-0.348: 0.640
-0.042: 0.441
-0.137: 0.432
-0.138: 0.418
0.107: 0.636
0.134: 0.630
0.118: 0.655
0.136: 0.641
0.228: 0.756
0.252: 0.769
-0.174: 0.278
0.045: 0.415
0.072: 0.082
-0.227: -0.163
0.233: 0.498
0.311: 0.570
0.096: 0.493
0.138: 0.353
0.160: 0.389
0.100: 0.360
0.185: 0.355
0.177: 0.328
0.265: 0.265
0.010: 0.339
0.193: 0.245
0.080: 0.204
0.141: 0.249
0.117: 0.267
-0.148:-0.023
-0.124:-0.053
-0.154:-0.054-0. U8:-0.058
-0.231:-0.126
-0.167t-0.065
-0.132:-O.OS1
-0.123:-O.U81
-0.274:-0.142-0.29U-0.107
0.346: 0.768
0.479: 0.764
0.486: 0.777
0.402: 0.782
0.486: 0.821
0.226: 0.514
0.293: 0.864
0.121: 0.598
0.094: 0.584
-0.020: 0.696
BURNOUT HEAT
FLUX KANOE
-B/SiiCB
263.0: 560.0
256.0: 510.0
442.0: 525.0
175.0: 407.0
93.0: 326.0
128.0: 140.0
loO.O: 280.0
221.0: 500.0
U6.0: 3V6.0
61.0: 314.0
128.0: 430.0
57.6: 374.8
47.5: 35b.2
56.8: 493.551.0: 401.7
63.1: 165.3
48.2: 269.7
45.0: 327.4
51.1: 368.1
47.3: 487.4
46.4: 199.7
45.1: 212.0
20.7: 314.8
31.5: 292.1
36.6: 255.2
11. 8: 36.3
25.2: 97.8
55.5: 86.8
135.5: 335.195.3: 191.2
93.7: 163.7
45.1: 212.0
72.6: 202.2
53.6: 242.9
51.4: 2.36.3
91.6: 213.0
90.5: 239.7
90.4: 209.1
b8.2: 229.7
24.0: 150. V
22.8: 123.9
143.2: 493.1
69.1: 184.8
108.7: 117.7
87.3: 118.7
56.2: 109.4
71.2: 150.187.1: 289.6
49.4: 143.5
64.5: 175.8
35.4: 123.8
25.1: 72.4
76.6: 138.4
111.3: 111.3
89.2: 415.9
109.5: 215.8
183.8: 332.7
178.2: 285.7
151.0: 292.8
379.8:1144.2
470.0M1S6.2
421.5:1240.1709.8:1053.9
1277.6:2220.2878.6:2036.9
471.9:1611.0
577.9:1389.0
255.5: 880.1
1101.6:1858.1
2.4: 59.7
10.9: 65.4
4.2: 16.4
4.4: 21.87.1: 21.8
64.7: 150.6
6.4: 69.4
27.0: 241.6
31.7: 388.0
18.8: 201.7
TABLE 2C
MEANINGS OF SYMBOLS USED TO INDICATE SPECIAL FEATURES OF ASSEMBLIES
SYM.
E
L
si
Dy
N
I
NO.
OF
:
i_
92
08
48
33
31
16
13
11
10
8a
8
4
4
4
44
33
21
1
1
1
1
NO.
OF
4S41
3446
2340
1C24
1359
544
4C8
121
172
404
370
173
168
226
212
75
55
37
17
10
23435
24
21
21
1815
5
LEANING
J I.
NCN-CIRCULAS DUCT.
SQUARE PITCH ARRAY.
TRIANGULAR PITCH ARRAY.
DUCT PROTUBERANCES SIMULATING EITHER A PART OF THE SURFACE OF SURROUNDING RODS OR
THE BOUNDARY OF ADJACENT ROD CELLS.
SEVEN-ROD BUNDLE ENCLOSED IN CIRCULAR DUCT.
HEATED DUCT.
ASYMMETRIC AXIAL DISTRIBUTION OF HEAT FLUX WITH PEAK IN DOWNSTREAM HALF OF CHANNEL.
CONSTANT HEAT FLUX MAINTAINED ON PART OF HEATED SURFACE.
SEPARATED STEAM AND MATER PHASES AT INLET TO CHANNEL.
OOMNFLOM CF CCCLANT.
BURNOUT NOT AT OUTLET OF CHANNEL WITH AXIALLY UNIFORM HEAT FLUX.
STEPPED PROFILE Of- AXIAL DISTRIBUTION OF HEAT FLUX.
ASYMMETRIC AXIAL DISTRIBUTION OF HEAT FLUX wITH PEAK IN UPSTREAM HALF OF CHANNEL.
BUNDLE MOUNTED ECCENTRICALLY IN DUCT.
PGD TC DUCT GAP REDUCED BY ROD BOnlNG OR ATTACHMENT OF PADS TO DUCT WALL.
HORIZONTAL CHANNEL.
HEAVY WATER COOLANT.
RODS CONVERGE TOWARDS DOWNSTREAM END OF BUNDLE.
NATURAL CIRCULATION OF COOLANT.
SPIKE CR HOT PATCH IN AXIAL DISTRIBUTION CF HEAT FLUX.
HEAT FLUX TILT ACROSS SOME RODS IN BUNDLE.
CrtUD DEPOSIT DELIBERATELY FORMED CN RODS BEFORE TEST.
MISALIGNMENT OF RODS IN ADJACENT AXIAL SEGMENTS OF BUNDLE.
TWO RCOS IN CONTACT.
ROD GAP REDUCED BY BOWING OF ROD.
PARTIAL BLOCKAGE OF COOLANT FLOW PASSAGE.
SIGNIFICANT HEAT LOSS FRCK DUCT.
BUNDLE CONTAINS HEATED RODS OF DIFFERENT DIAMETERS.
cnCO
TABLE 2D
GRID OR ROD SPACER TYPES AND REFERENCE NUMBERS
UJ
REF. I MO. I NO.
NO. I OF | OF
1ASS1S1-IES1SI I
1.0 I
1.1 I
"sto'i"
3.1 I
1.2 I
3.3 I3.4 I
-__5_l.
4.0 I4.1 I
4.2 I
5.0 I
__i.l_l6.0 I
<?.! I
..6*2-17.0 I
? j?i_i
8.0 J
d.l I
8.2 I
--JJ.J-I
9.3 I
10.0 (10.1 I
.10*2-111.0 I
11.1 I11.2 I
11.3 I
11.4 I
11.5 I
I
8 I
Ir
34 I
33 I
8 I
10 I
?4-1.
I
V I6 I
"13" r?1-1.
I
3 I
~24~f
-_5_i.
1 I5 I
r~32~r
3 I
?2-1
6 I
II
2 I2 I
I
l_i_
1CC31151
272375
570209
1117
4j_
^77
_22614CS
633
140
1365
90
_ iO_
?18
46
4*
.__ ___ __
13.0 I 2 I 291
15.0 I
15.1 J
_i6*r
I
31i_i
L2_i
87
107
17.0 I17.1 I
17.2 I
_
I
21
8 I
71
216
GRID TYPE
WRAPPED WIPE INU.-BER UF GRIDS * NUMBER OF COMPLETE TURNS):
MCLND CFPOSITE HAND ON ADJACENT RODS.
hOUND ON BINDLE ONLY.
RADIAL PINSt "ARTSt OR STUOS ATTACHED TO RODS OR OUCT:CUCT-TO-ROO CNLY.
ROO-TO-ROO ANO OUCT-TO-HOO.
ROO-TO-ROO CNLY.
UUCT-TO-POC. PLUS AXIAL TUBES ROO-TO-PUO.
aQ_=ia=BOQ_iiU.-QUCI=IU_Bflfi-_SIA_G_B?___AlALLX,i
AXIAL PIAS OR TUBES ATTACHED TO RODS OR DUCT:
OUCT-TU-ROO CNLY.RCC-TO-ROO AND C'lCT-TO-ROO.
A*IAl TUBES 1NTSPCCNC4ECTEO TO FCP" GRID.
BCD=i?ACJl?li-BlIilS5_lW?BCCMlll??I?E_JO-?08H.CBi
eeffit PLATES:
FUCL PLATE tilTH CUT-OUT FLCrt ORIFICES.
O1
<?>
IM-ERCCM.'ECrEC RCO-SURROUNUfNC Rlf.GS WITH PADS. WAfiFS. OR TONGUES.
ROO-IMEf)?E?VING BANDS MtTH PADS.
CCRRUGATEO STRIPS (PARALLEL TO A ROD PITCH LINE* HfTH TONGUES.CGKRI.GATEC STRIPS CPERPENCICULAR TO A ROD PITCH LINE! ulTN TONGUES.
FILM-STRIPPING RING ATTACHED TO OUCT HALL.
EGG-CRATE OR HONEYCOMB OS JDS *ITH PADS OR TCNOUESi WITHOUT MIXING VANES:
SIHPLE SUPPORT.
EGG-CRATE OR HGNEYCOMB GRIDS HlTh PADS OR TONGUES AND MIXING VANES:
SIMPLE SUPPCRT.
kESTINGHOUSE T-H.
NO PERIPHERAL VANES.
T-Hi NO PERIPHERAL VANES.
EGG-CRATE OR HONEYCOMB GRIDS WITH PADS OR TONGUES AND MIXING SCOOPS:
HO P^h.lPMEfW, SCn?Ps-
_BJJ)S.MlIU_fiJCiAL_SIBi_..__ROD-GRIPPING SLEEVES MlTH INTERCONNECTING PAUS.
CHORCAL STRIPS:ROC CONTACTED ON ONE SIDE CNLY.
BAND OR SLEEVE -RAPPING BUNDLE CIRCUMFERENCE. ___
SEPARATE SPRING SLEEVES ATTACHEC TO RODS:
SINGLE FLOta kINOOM.
DOUBLE FLOk HlNOOM.
60
TABLE 3A
COMPOSITION OF THE DATA BANK IN RESPECT OF ROD ARRANGEMENT
Form of Rod Arrangement
Circular pitch *
Square pitch
Triangular pitch
(7- rod within circular
duct) f
2-rod, not simulating
square pitch
Single rod with non-
circular duct
Annulus
All forms
Numbers of Tests included for Assemblies with:
Axially Uniform
Heat Flux
4604
2850
2279
(1352) f
65
189
895
10 882
Axially Non-uniform
Heat Flux
559
596
61
( 7)*
0
0
375
1591
All Distributions
of Heat Flux
5163
3446
2340
(1359)#
65
189
1270
12 473
# Item and numbers enclosed in brackets are included in the circular pitch
class.
* See Glossary for definitions of terms.
TABLE 3B
SUBDIVISION OF ROD ARRANGEMENT CLASSES ACCORDING TO NUMBER OF RODS
Circular Pitch Arrays
Number
of Rods
is
6
7
19
37
ALL
Number
of Tests $
211 [ 87]
30 [ 0]
1359 [ 7]
1731 [ 45]
1832 [420]
5163 [559]
Square Pitch Arrays
Number
of Rods
2+
4
5
9
16
20
21
25
ALL
Number
of Tests?
68 [ 0]
222 [ 0]
3 [ 3]
1932 [189]
824 [404]
103 [ 0]
71 [ 0]
223 [ 0]
3446 [596]
Triangular Pitch Arrays
Number
of Rods
3
7
<7)?
12
19
20
24
29
ALL
Number
of Tests5
1151 [ 18]
298 [ 0]
(1359 [ 7])#
51 [ 0]
20 [ 0]
809 [ 32]
5 [ 5]
6 [ 6]
2340 [ 61]
Notes to Table 3B
? simulating central rod in a circular pitch array.
4- simulating square pitch.# enclosed in circular duct; numbers included in total for circular pitch
array.$ numbers of tests with axially non-uniform heating are enclosed in square brackets.
61
TABLE 3C
COMPOSITION OF THE DATA BANK IN RESPECT OF THE SHAPE OF THE ASSEMBLY DUCT
Shape of Duct Cross-Section
*Circular, no P
Circular, with P
All circular shapes:
Rectangular, no P
Rectangular, with P
All rectangular shapes:
Cruciform
Paral lelogrammatic, no P
Parallelogrammatic, with P
All parallelogrammatic sh
Hexagonal, no P
Hexagonal, with P
All hexagonal shapes:
Triangular
All shapes
Number of Tests included for Assemblies with:
Axially Uniform
Heat Flux
5891
689
6580
2855
68
2923
71
729
99
apes : 828
341
76
417
63
10 882
Axially Non-uniform
Heat Flux
865
87
952
593
0
593
3
32
5
37
6
0
6
0
1591
All Distributions
of Heat Flux
6756
776
7532
3448
68
3516
74
761
104
865
347
76
423
63
12 473
* P = protuberances, simulating either part of the surface of surrounding
rods or the boundary of adjacent rod cells.
TABLE 4A
COMPOSITION OF THE DATA BANK IN RESPECT OF HEAT FLUX DISTRIBUTION
Radial
Distribution
Uniform
Non-uniform
All radial
distributions
Number of Tests included for Assemblies with:
Axially Uniform Distribution
Burnout
at Exit
5909
4709
10 618
Upstream
Burnout
188
76
264
Axially Non-uniform Distribution
Position of
Burnout
Detected
712
795
1507
Position of
Burnout
Not Detected
30
54
84
All Axial
Distributions
6839
5634
12 473
a\ro
63
TABLE 4B
SUBDIVISION OF TESTS WITH AXIALLY NON-UNIFORM HEATING ACCORDING TO FLUX PROFILE
Position of
Peak
Towards inlet
Symmetrical
Towards
outlet
All positions
of peak
Number of Tests included for Assemblies with Axial Heating
Profiles of the Form:
Smooth
79
1015
314
1408
Step ! Spike
80
0
93
173
9
0
1
10
All Types
168
1015
408
1591
TABLE 4C
DISTRIBUTION OF TESTS BETWEEN ASSEMBLIES WITH UNHEATED AND HEATED DUCTS
State of Duct Heating
Unheated duct
Heated duct
All states
Number of Tests included for Assemblies with:
Axially Uniform
Heat Flux
10 473
409
10 882
Axially Non-uniform
Heat Flux
1456
135
1591
All Distributions
of Heat Flux
11 929
544
12 473
64
TABLE 5
DISTRIBUTION OF BURNOUT TESTS ACCORDING TO PHASE CONDITION OF THE COOLANT
Condition of Coolant
Subcooled or satur-
ated water at burn-
out section
Subcooled or satura-
ted water at inlet,
steam-water mixture
at burnout
Subcooled or satura-
ted water at inlet
Steam-water mixture
at inlet,
uniformly mixed
Steam-water mixture
at inlet, non-
uniformly mixed
i Steam-water mixture
at inlet(
1 All conditions
Number of Tests included for Assemblies with:
Axial ly Uniform
Heat Flux
1255
8584
9839
933
110
1043
10 882
Axially Non-uniform
Heat Flux
305
1206
1511
30
50
80
1591
All Distributions
of Heat Flux
1560
9790
11 350
963
160
1123
12 473
65
TABLE 6A
COMPOSITION OF THE DATA BANK IN RESPECT OF UNUSUAL OR ABNORMAL FEATURES
OF THE TEST ASSEMBLY
Assembly
With unusual or
abnormal features
Without unusual or
abnormal features
All assemblies
Number of Tests included for Assemblies with:
Axially Uniform
Heat Flux
988
9894
10 882
Axially Non-uniform
Heat Flux
87
1504
1591
All Distributions
of Heat Flux
1075
11398
12 473
TABLE 6B
NUMBERS OF TESTS ASSOCIATED WITH INDIVIDUAL FEATURES
Feature
Unusual features:
Horizontal arrange-
ment
Downflow
Natural circulation
Heavy water coolant
Converging rods
Abnormal features:
Eccentric bundle
Bowed rod
Rods touching
Reduced rod-shroud
clearance
Misalignment in
segmented bundle
Flow obstruction
Crud deposit
Number of Tests included for Assemblies with:
Axially Uniform
Heat Flux
75
404
10
55
37
226
21
21
132
24
18
35
Axially Non-uniform
Heat Flux
7
80
All Distributions
of Heat Flux
75
404
17
55
37
226
21
21
212
24
18
35
TABLE 7
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
)IV. RANGE Of G
G/S.SOCM
1
2
3
4
5
67
8
9
10
11
It13
1415
16
17
18
1920
21
2223
24
2526
2728
2930
31
32
0.0 :
50.0001:
100.001:
150.001:
200.001:
250.001:
300.001:
350.001:
400,001:
450.001:
500.001:
550.001:600.001:
650.001:700.001:
750.001:
800.001:
850.001:
900.001:950.001:
1000.01:
1050.01:
1100.01:
1150.01:
1200.01:
1250.01:
1300.01:1350.01:
1400.01:
1450.01:
1500.01:
1550.01:
50.0000
100. CCO
150.000
200.000
250. OOC
300.000
350.000
400.000450. OCO
500.000
550. OCC
600.000650. OCC
700.000750. COC
800.000
850. OOC
900.000
950.000
1000.00
1050. CO
1100.00
1150.00
I 200. 00
1250.00
1300.00
1350.001400.00
1450. OC
1500.00
1550. CC
1600.00
RANGE OF P
MPA
0.0 :
1.00001:
2.00001:
3.00001:
4.00001:
5.00001:
6.00001:
7.00001:
8.00001:
9.00001:
10.0001:
11.0001:
12.0001:
13.0001:14.0001:
15.0001:
16.0001:
17.0001:
1.00000
2.00000
3.00000
4.00000
5.00000
6.00000
7.00000
8.00000
9.00000
10.0000
11.0000
12.0000
13.0000
14.00CO15.0000
16.0000
17.0000
13.0000
TABLE 7 (CONTINUED)
1
1 E_J
1 fi_1
^
34
5
6
7a
<y10
11
12
13
14
15
16
17
If,
I*
2C
21
22
23
24
25
26
27
28
2v
30
31
1 J2.J
1
555
29 !
6
17
5
14
?.
30
2oa
?i
?
?
? i
loO
15
11
23?
?.
?
13
5<J
)
3
6
3
L_ __!._ -,
_2
58 1'
)? :
t2 J
JO
? t
39
.3
K 34
U 1<
>?> I
LI '
> .
9
nr i
b2 2.
76 2.
42 <25 i:
3 ^
?
3
1 i i t
.5
rs 2
25 4.
J8 TiO <
)1 3<
?3 1<
7 !
>???.? U
_?
LI 2<
27 7,
?1 9.
?6 31
i7 3
>6 24
>6 it
W
4
.j
99
26 <
J5 1!
>8 '
34
i3 1
!>4
24 ,
23
1
_fl
14 1
>2 2.
>2 1<
? 3
f7
L3 <
31
23 i
t
^
.2 J
37 <
J3 I-
i7 !
?4
36 <
38
Li
L5
*7
LO
L92
?
3
10 J
)8
?3
>3 '
?4
bb
'
18 '
?
L2i ;
LI
17
27
?3
2
J3a
?3
12
16
26
12
15
3S <
26
6
LO
U '1
29
2
13
LO 1t3 2
28 2?4 1
j3 1
t7 1
10L7
11
22
14
53
!>4
27
29n
It,n
law
11
d
15
219 '
2 (8
5 '
25
25
5
32
23
Ift
14
U
il
30
'to
54
33
L5
10
7
12 ld_
L4
?3
24
4
14
27
33
3
24
L6 1
3
?
?
?
9
*
?
?
?
?
?
?
?
?
*
?
?
?
?
?
1 ?
TABLE 8
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUAL
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
)IV. RANGE OF OBO
W/SO.CM
1
2
3
45
6
7a
910
1112
13
1415
1617
1819
20
2122
2324
2526
2728
29
30
31
3233
34
3536
37
0.0 :
50.0001:
100. 001:
150.001:
200.001:
250.001:
300.001:
350.001:
400.001:
450.001:
500. OOi:
550. OCi:
600.001:
650.001:
700.001:
750.001:
800.001:
850.001:
900.001:
950.001:
1000.01:
1C50.01:
1100.01:
1150.01:
1200.01:
1250.01:
1300.01:
1350.01:
1400.01:
1450.01:
1500.01:1550.01:
1600.01:
1650.01:
1700.01:
1750.01:
1800.01:
53.0000
100. COO
150. OCC
200. COO
250.000
300. OCO
350. OCC
400. OOC
450. OOC
500. COO
550. CCO
600. CCO
650.000
700. COC
750. CCO
800. CCC
850.000
900. OOC
950. OCO
1000.00
1050. CC
1100.001150. OC
1200. CO1250. OC
1300.00
1350.00
14CO.OO
1450. OC
1500.00
1550.00
1600.00
1650.00
1700.00
1750.00
1800.00
1850.00
RANGE OF P
HPA
0.0 :
1.00001:
2.00001:
3.00001:
4.0C001:
5.00001:
6.00001:
7.00001:3.00001:
9.COOOI:
10.0001:
11.0001:
12.0001:
13.P001:
14.0001:
15.0001:
16.0001:
17.0001:
1.00000
2.00000
3.00000
4.00000
5.00000
6.00CCC
7.00000
8.00000
9.00000
10.00CO
11.0000
12.0000
13.0000
14.0000
15.0000
16.3000
17.0000
Id. 0000
OIV.
38
39
40
41
42
43
44
45
RANGE OF OBO
W/SO.CM
1850.01:
1900.01:
1950.01:
2000.01:
2050.01:
2100.01:
2150.01:
2200.01:
1900.00
1950.00
2000.00
2050.00
2100.00
2150.OG
2200.00
2250.00
00
- L
TABLE 8 (CONTINUED)
11 e_.
r
23
4?j
6
7
8v
10
11
12
1314
15
1617
18
IV
2021
22
23
24
25'
26
27
23
29
30
31
32
3J
3435
36
37
33
39
40
41
42
4344
L_45_J
1
432104
18
8
13
19
13
15
13
24
17
2o
1615
15
25
34
15
30
7110
21
12
6
d
5
1
5
21
5
1
6
1
1
11
1
2
^2
3.
.^
L 1 .,
1332
32 <
21
26
29
24
33
15
3
1 ? ____.!
_i_ A 5
2 131 69 210 275 341 8
95 196 247 6
iO 109 115 228 31 37 ?
9 17 27
19 13 10
443
3 5
1 1
3. .
1
1. .
? *
? *
. 9
, ?
. .
^ 9
? *
? *
? ?. .
. f
. .
* *
* ?
? *
? ?
? *
? ?
? ?
? ?
? *
* ?. .
? ?. .
? ?
? ?
? ?. .
L ,, j?___ >
6
91
3981
:7ba
2117
7
3
3
_
 2
 76  9
C7 6
68 3
 1(
_z
t3
b6
03 I?*
15
31J4
12
2
2
-B__ .
t>9
76 113 1
73 ' 1?5
25
13
1
.3
c>4
1280
74
95
5317
13
7
5
1
1
10
6
21
48
47%7 '
iV4to
22
t4
29
?0
?2
11
9
2
2
1
2
11
1
303-*
i7
is
3325
9
5
3
L2
24
2633
24
9
7
1
2
1
13
13 2-
32 2
s?4 2<
U7 1-
<?8 I
JO
16
7
7
21
2
?
1
14_ _.
23
V377
)1
*2
i7
J3
175
8
53
15
? 8
19
24
2o
2928
9
2
1
16
4
57b5
77
78
?2
7
1
k. ?? J
11
10
3535
?5
35
14
16
3
2
18_
?
1
10
TABLE 9
DISTRIBTUION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
CIV. RANGE OF
G/S.SOCP
RANGE OF 060
M/SO.CM
1
2
J
4
5
6
7a
910
11
12
13
14
15
16
17
Id
19
20
2122
2324
25
2627
2829
30
3132
0.0 :50.0001:
100.001:150. OCl:
200.001:250.001:
300.001:350.001:
430.001:450.001:
500.001:550.001:
600.001:650.001:
700.001:750.001:
800. OCl:850.001:
900.001:950.001:
1000.0 I :1050.01:
1100. 01:1150.01:
1200.01:1250.01:
1300.01:1350.01:
1400.01:1450.01:
1500.01:1550.01:
53.0000100. 000
150. CCC200. CCG
250 .000300. OCC
350. GCC400. OCO
450.030500. OCC
550. OCC600.000
650. OCO700. COO
750. OCC800. OCO
850. CCC900.000
950. OOC1000.00
1050. CC1100. CO
1150. CC1200. CC
1250. CC1300.00
1350. OC
14CO.CC1450. OC
1500. CC
1550. CC
1600. OC
O.C :100. 001:
200.001:300.001:
400.001:500.001:
600.001:700.001:
800.001:900.001:
1000.01:
1100.01:1200.01:
1300. 01:14C0.01:
1500.01:1600.01:
17C0.01:1800.01:
1900.01:
2000.01:21C0.01:
2200.01:
100.000200.000
3CO.OOO400.000
500.000600.000
7CO.OOO800.000
900.0001000.00
1100.001200.00
1300.001400.00
1500.00
1600.00
17CO.OO
1800.00
1900. CO
2000. 00
2100.002200.00
2300.00
TABLE 9 (CONTINUED)
TABLE 10
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
ThP SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
CIV. RANGE OF RANGE OF XBO
G/S.SOCM
12
3
4
5
6
7
d
S
10
11
1213
14
15lo
17ia
19
20
21
2223
24
2526
2728
2930
3132
0.0 :
50.0001:
100.
150.
200.
250.
300.
350.
400.
450.
500.
550.
600.
650.
7CO.
753.
80C.
650.
900.950.
1000
1050
1100
1150
1200
1250
1300
1350
1400
1450
1500
1550
001:
001:
001:
001:
001:
OCl:
001:
301:
001:
001:
001:ecu
001:
001:
001:
001:
OCl:001:
.01:
.01:
.01:
.01:
.01:.01:
.01:.01:
.01:
.01:
.01:
.01:
50.0CCO
100.000150.
200.
250.
300.
350.
400.
450.
500.
550.
600.
650.
700.
750.
800.
850.
VOO.
950.1000
1050
1100
1150
1200
1250
1300
1350
1400
1450
1500
1550
IbOO
OOC
OCOCOO
COOOCO
OCOocc
OCO
000occ
ceoceo
ceoocc
occocc
OCO.cc
.00
.00.00
.00.00
.00.cc
.00.oc
.00
.oc
.00
-0.
-0.-0.
-0.
-0.
0.
0.
0.0.
0.
0.
0.
0.
0.
0.
500QO:-0
39999: -0
29999: -0
19999:-0
.40000
.30000
.20000
.10000
09999:-0. 00000
00001:
10031:
20001:
30001:
40031:
50001:
60001:
70001:
8C001:
90001:
0
00
0
0
0
00
01
.10000
.20000
.33000
.40000
.50000
.60300
.70000
.80000
.90000
.03003
TABLE 10 (CONTINUED)
TABLE 11
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUAL
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OP TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF G
G/S.SCCH
RANGE OF XIN
1
2
3
4
5
67
89
10
1112
1314
1516 '
17
1819
20
2122
2324
25
2627
2d29
30
3132
C.O :
50.0001:100.001:
150.001:200.001:
250.001:300.001:
350.001:
400.001:450.001s
500.001:550.001:
600.001:650.001:
700.001:750.001:
800.001:850.001:
900. 001 :S50.001:
1000.01:1C50.01:
1100.01:1150.01:
1200.01:1250.01:
1300.01:1350.01:
1400.01:1450.01:
1500.01:1550.01:
50.0CCO
100.000150. CCC
200. OCC250. OCO
300.000
350. OCO400. COO
450. OCC500. OCO
550. OOC600. OCC
650. OCO700. COO
750. COOaoo.occ
850. CCO
900. OCO
950.000
1000. CC
1050. CC
11CO.CO
1150. CC
1200. CO
1250. OC
1300. CO
1350. CC
1400. CO
1450. OC
1500. CO
1550. OC
1600.00
-1.10000:-1.00COO
-0.99999:-0.900CO
-0.89999: -0.80000
-0.79999:-0.7000C
-0.69999:-0. 60000
-0.59999: -0.50000
-0.49999: -0.40000
-0.39999: -0.30000
-0.29999:-0.200CO
-0.19999: -0.10000
-0.09999: -0.00000
0.00001: 0.10000
0.10001: 0.200000.2C301: 0.30000
0.30001: 0.40000
0.40031: 0.500000.50001: 0.60000
0.60301: 0.70000
0.70301: 0.80000j. 90001: 0.90COO
TABLE 11 (CONTINUED)
1
1 XJN-J
1 ?_1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
2?
23
24
25
26
27
2fl
29
30
31
1__32_J
1
|
1
i
17
14
13
2
4
4
1
1
1
.3
4
3
? 1
2
LO12 <
6 <
6
2
.5
55
>1 '
?7
17
L6
Zl
2
1
6
1
2
.6 2 a a.
36 88 207 432
.5 116 226 334
)2 67 187 301
L5 40 81 105
25 51 104 134
LI 48 101 124
1 10 38 75
1 6 12 33
1 6 29 83
9 27
1 15 6
1. .
1
? ?. .
.
14
1 2
135
2 18
.
9
9
.
.
8
^ ,
1
1 5
3
? I
_a 10. 11 i
>3  543 796
3  692 731
0  974 907 1'
0  214 307 !
3  429 455
2  281 360 '
7  103 2013  52 48
8  141 422  63 26
6 10 4
1
112.
1 136 10
2 125 2
1
13 49 1
9 2
5
X_ .* * j
L2
J3ro
>7 i
52rs
?o
13
L4
5
13
877
i3 !
26to
5
8d
14.
7
50
54
6
203
4
1
15
4
L3
J9 '
7
7
3
3
16
6)1 .
kl
12
d2
LI
327
>0
12I
1
Lu??*??.4
4
19
L9
3
ia -
1L2
6
2
20_
.
25
1
en
TABLE 12
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUAL
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12473
THF SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV.
1
2
3
4
5
6
7
8
}
10
11
12
1314
15
lo
17
IS
19
20
21
22
23
24
25
26
27
23
29
30
31
32
RANGE OF G
G/S.SOCH
0.0 :
50.0001:
ICO.001:
150.001:
200.001:
250.001:
300.001:
350.001:
400.001:
450.001:
500.OCl:
550.001:
600,001:
650.001:
700.001:
750.001:
800.001:
850.001:
900.001:
S50.001:
1000.01:
1050.01:
1130.01:
1150.01:
1200.01:
1250.01:
1300.01:
1350.01:
1400.01:
1450.01:
1500.01:
1550.01:
50.0COC
100.000
150.CCO
200.000
250.COG
300.000
350.CCO
400.000
450.000
500.OCO
550.OCO
600.OCO
650.OCO
700.COC
750.OCO
800.CCO
B50.000
900.OOC
950.OCO
1000.00
1050.OC
1 ICO.00
1150.OC
1200.00
1250.OC
1300.CO
1350.CC
1400.00
1450.OC
1500.CO
1550.00
1600.00
RANGE Of HEQO
MM
2.00000:
5.00001:
8.C0001:
11.0001:
14.0001:
17.0001:
20.0001:
23.0001:
26.0001:
29.0001:
32.0001:
35.0001:
38.0001:
41.&001:
44.0001:
47.0001:
50.0001:
53.0001:
56.0001:
59.0001:
62.0001:
65.0001:
68.0001:
71.0C01:
74.0001:
77.0001:
80.0001:
83.0001:
5.00000
8.00COO
11.0000
14.0COO
17.0000
20.0000
23.0000
26.0000
29.0000
32.0000
35.0000
38.0000
41.0000
44.0003
47.0000
50.0COO
53.0000
56.0000
5V.OOOC
62.0300
65.0003
68.0000
71.0300
74.00CC
77.0000
80.0COO
83.0000
86.0000
en
i
TABLE 12 (CONTINUED)
1
lifJSD.J1 G_
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
18
19
20
21
22
23
24
25
26
27
2U
29
30
31
l_~32_J
1:__.
<
4
l__
.1
31 554 1<
i7 2
1 1
*9 1
J4 t
15
Lt) .
17 .
7d
1
.,
.2 ?
53 4iC 5<
27 8
L8 <
21 2
*6 220
J5JO
7
4
, j
_3 A
82 91 2<
!>0 6C8 2
J9 828 1
;5 182 1.
59 646
C8 464 l<
19 29C
d3 31
52 49 ?
3 29
L5 .
1 .
1
3 .
?
?
?
.
?
*.
?.
?.
?
?
?
?
?
.
.5 ?
V7 323 :
51 518 'i6 60U '
2J 192 I57 1C4 .
51 46
DO .=.9 20
iS 51
71 d
2
35
3
11
13
14.
3
1.
-? -?
JO 1
J4 <
t9
39 '
>1
8
12
?19
12
1
HI II I 1 1
.& s_
11 . 155 17
36 Id
?2 3717 19
11 51 2
.
46
9
6
12512
*
20
44
9.
53
i_ J
JLQ 11 ? l2__13_.14__J5__16__12__lfl_.13? 2D__21__ 22__23._24-_25._26__22._2fl_
26
135
46 5 5 118 41 22 2
86 1 10 38 17 17 19
11
3
t.-_J
1196
4 . 32 20 b
*
20
11
? ? ?
8 ? ?17 3 35
13 20 27
9 .
1 .
*
*
*
?
?
?
?
?
?
?
*
*
25
TABLE 13
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12469
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF RODS RANGE OF G
G/S.SOCM
1
2
3
4
5
67
a
9
10
11
12
13
14
1516
1718
1920
21
22
2J24
2526
27
28
29
30
31
3233
34
35
3637
C. 50000:1.50001:
2.50001:
3.50001:
4.50001:
5.50001:
6.50001:
7.50001:
8.50001:
9.50001:
10.5001:
11.5001:
12.5001:
13.5001:
14.5001:
15.5001:
16.5001:
17.5001:
18.5001:
19.5001:
20.5001:21.5001:
22.5001:23.5001:
24.5001:25.5001:
26.5001:
27.5001:
28.5001:
29.5001:
30.5001:
31.5001:
32.5001:
33.5001:34.5001:
35.5001:
36.5001:
1 . 500002.50000
3.50000
4.5000C
5.5000C
6.50000
7.50COC
8.500CC
9.5000C
10.5000
11.5000
12.5000
13.5000
14.5GOC
15.500C16.5000
17.50CO18.5000
19.5CCO20.5000
21.5000
22.5COC
23.5CCO24.5000
25.500026.500C
27.50CO
28.5000
29.50CO
30.5000
31.5000
32.500C
33.5000
34.5000
35.5000
36.5030
37.5000
0.0 :50.0001:
100. 001:
150.001:
200.001:
250.001:
300.001:
350.001:
400.001:
450.001:
500.001:
550.001:
600.001:
650.001:
700.001:750.001:
800.001:850.001:
900.001:
950.001:
1000.01:1050.01:
1100.01:1150.01:
1200.01:1250.01:
1300.01:
1350.01:
1400.01:
1450.01:
50.0000100.000
150.000
200.000
250.000
300.000
350.000
400.000
450.000
500.000
550.000
600.000
650.000700.000
750.000
800.000
850.000
900.000
950.0001000.00
1050.00
1100.00
1150.001200.00
1250.00
1300.00
1350.00
1400.09
1450.00
1500.00
00
9
ot
?
M
6 81
' 11
\ fl
' 9<
i
' 21
Ot
' I<
r ii
r 02
51
' 61
0^
01
,1 1
r JL1 91 51
1 ? ? ? ? ? I ' IT boi si? t*mr 5*5T:z$ B<
? I ? 6 f 9E 9 65 V* ZI i? 91
? II 6 ?5 ? 9 1Z1 Z8 91 UZ 1C? LI
C ? t 8 * I> 91 SI 651 Z*l SL fZS 00^ fll
? Z It Ob ZI *S 9*- 6Z 9P *IZ ZPT 6(
IBZiS ? It * * 9 Q '
? i ts cv 6 LB 59 evi ?zz rp?7 ees zt
? ? - -I - fi? ZZ ^ OtZ ZOI ^ir 09Z 9J
? 1 51 ' * /S ZS 9i 1Z1 661 Si
? 8 ZI 001 iC 5*1 691 85? 66 P97 9/1 ?{
r f T cr ?T~rr or-5~-B-T 9-5-^ r r T
.1ie
n
t
?z
;9
.
.5
>
r rr i
9t
SF
*fte
?i
IE
OC
6Z
HZ
J.Z
9Z
SZ
VZ
EZ
(.2
IZ
61
HI
/I
91
bl
VI
tl
II
01
fr
^99
t
i
I
-COO?rg ?
ei 3iavi
TABLE 14
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE*
;IV. RANGE OF RODS RANGE OF P
MPA
1
2
34
5
6
7
8
9
10
11
12
13
I*
1516
17
1319
20
2122
2324
25
2627
2829
30
31
3233
3435
3637
0.50000:
1.50001:
2.50C01:
3.50001:
4.50001:5.50001:
6.50001:7.50001:
8.50001:
9.50001:
10.5001:
11.5001:
12.5001:13.5301:
14.5001:15.5001:
16.5001:
17.5001:18.5001:
19.5001:
20.5001:
21.5001:
22.5001:
23.5001:
24.5001:
25.5001:26.5001:
27.5001:
28.5001:
29.5001:
30.5001:
31.5001:
32.5001:
33.5001:34.5001:
35.5001:36.5001:
1.50000
2. 5000 C
3.5000C4.50COC
5.50COO6.5000C
7.50COC
8.50000
9.50COC
10.5000
11.50GC
12.5000
13.500014.5000
15.5COC
16.5COC
17.50CO
18.5COO19.5000
20.5COO
21.5000
22.5000
23.5000
24.500025.5COO
26.500027.5000
28.500029.5000
30.500C
31.5000
32.500033.5000
34.500035.50CO
36.500C37.5000
0.0 :
1.00001:
2.00001:3.00001:
4.00001:5.00001:
6.00001:
7.00001:
8.00001:
9.00001:
10.0001:
11.0001:
12.0001:13.0001:
14.0001:15.0001:
16.0001:
17.0001:
1.00000
2.00000
3.00000
4.00000
5.000006.00000
7.000008.00000
9.00000
10.0000
11.000012.0000
13.000014.0000
15.000016.3000
17.0000
18.0000
00o
I
TABLE 14 (CONTINUED)
11 ?_.
l"
2
3
<t
?>
6
7
3
9
10
11
12
13
14
15
10
17
18
19
23
21
22
23
24
25
26
27
2S
24
30
31
32
34
i 351 36
L__32_J
1 1 _2
404
? ?125 157 1
2<3 55
? ?
? ?4c3 12 '
? *
? *
? *
? ?
? ?
? *
? ?
? *
? ?
? *
? *
? *
* *
? ?
? ?
? *
? ?21
? ?
* ?
? ?
* ?
? *
? ??
? ?
* ?
? ?L * .. J
.3 4 5 _
7 . I'
891 259 114
? ? ?
11 14
?4 159 Ii8 3
? ? ?
5 39 I'
? ? ?
? ? ?
? ? ?
? ? ?
? ? *
19 '
? ? *
? ? ?
1 245 65 7
7
2. .
? ?. .
? ?? ?
. .
? ?
? ?? ?
? ?? ?
? .
? ?. .
L7. ... 52.. ft 30 ..6
.6 2 fl
53 575 133 ;4 49
38 65 59
74 10
577 238 97
U 465 79 l<
? * ?
? * ?
!
? * * 4
? * ?
? * *
?2 493 21 I
? ? ?
? ? ?L6 475 15 2
4 . 2i4 11
* *
. .
? ?
. 9
9 *
? ?
? ?. .
. .
. .
?
0 m
. .
* ?3_ 5B2- 1
9 ifl ii_ iz u 14 15 16 12 _ 18
26 156 17 9 76 *> 1 178 . 30 34
16 127 10 .
51 . .
3 ....?????????.
33 . 59 57
????*?***?
28 93 98 18 94 335 56 232 129
>.........
>. T. ......
51 .........
????:??????
????????*?
???*?????*
L3 . 54 1 30 1 89 55 I
>...*...............
14 . 20 .......
J8 3 90 . 52J ....9 . 45 .......
.........
.5 ....
13 9 41 7o 62 1 .
...A.....
.........
.
.... 6....
.........
.
.
***??????
? *???????
? ????????
TABLE 15
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF RODS RANGE OF HEOD
MM
1
2
3
45
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
2128
2930
21
32
33
34
35
36
37
0.50000:
1.50001:
2.50001:
3.50001:
4.50001:
5.50001:
6.50001:
7.500CI:
8.50001:
S.500C1:
10.5001:
11.5001:
12.5001:
13.5001:
14.5001:
15.5001:
16.5001:
17.5001:
18.5001:
19.5001:
20.5001:
21.5001:
22.5001:
23.5001:
24.5001:
25.5001:
26.5001:
27.5001:
28.5001:
29.5001:
30.5001:
31.5001:
32.5001:
33.5001:
34.5001:
35.5001:
36.5001:
1.5000C
2.50000
3.5COOC
4.5000C
5.50CCC
0.500CC
7.50000
8.5000C
9.500CC10.5CCC
11.5GCO
12.5000
13.500C
14.5000
15.5000
16.5000
17.500C
18.50CO
19.5000
20.5000
21.5COO
22.50CC
23.5000
24.500C
25.5COO
26.5COC
27.50CC
28.5000
29.5COO
30.500C
31.5000
32.5000
33.5000
34.5000
35.5000
36.5000
37.5000
2.00000:
6.00001:
10.0001:
14.0001:13.0001:
22.0001:
26.0001:
30.0001:
34.0001:
38.0001:
42.0001:
46.0001:
50.0001:
54.0001:
58.0001:
62.0001:
66.0001:
70.0001:
74.0001:
78.0001:
82.0001:
6.00000
10.3000
14.0000
18.0000
22.0000
26.0000
30.0000
34.00CO
33.0000
42.0000
46.0009
5C.OOOO
54.0000
58.3000
62.0COO
66.0000
70.0000
74.0000
78.0000
82.0000
86.0000
03ro
L
TABLE 15 (CONTINUED)
1
1B?QD-1 1 2 3- 4_ 5 6 JZ 8
lEJQDS.
1
2
3
4
5
6
7
3
V
10
11
12
13
14
16
17
Id
19
20
21
22
23
24
2t>
26
27
28
2-?
30
31
32
33
34
3536
71 94 73C 109 178 48 30415 10 B8
199 3fld 153 98 13 147 S3 45 4
? ? * 3 ? ?21
82 746 455 18 198 66
? ? ? * * ?2 651 ?75 718 122
.....? ....
51 ....
? ? ? * *
* ? ? ? ?
II. 325 499
? ? * ? ?
? ? ? * ?. 1510 230 11
294 515 . . 103
? ? 11 oO ?? ? ? * ?
* * ? ? ?* 5 * ? ?
21 202
? ? ? ? *
? <*???
? ? ? ? ?
6 ? ? ? ?
? ? ? * *
? ? ? i ?
? ? ? ? *
? ? ? ? *
* ? * ? ?
? ? ? ? *
? ? ? ? ?
4
1 32_1 * 265_1?2J ? _ *_ ? . __
9
1& ?..J
UJ
1
6
U
13
99
2
12
? i
20
23
9
29
13
23
9
39
L4 JL5 16 U _.
8
ia j
3
>2
IS ,2J3 -jn
5
. 1
1
I
CD
CO
TABLE 16
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
CIV. KANGE OF RUIA
MM
RANGE OF HEOD
MM
1
2
34
5
6
7
8
9
10
11
12
13
1415
16
17
18
19
20
21
2223
24
25
26
27
C.O :
2.00001:
4.00001:
6.00001:
8.0C001:
10.0C01:
12.0001:
14.0001:
16.0001:
18.0001:
2C.0001:
22.0001:
24.0001:
26.0001:
28.0001:
30.0001:
32.0001:
34.C001:
36.0001:
38.0001:
4C.C001:
42.0001:
44.0001:
46.0001:
48.0001:
50.0001:
?2.0001:
2.COOCC
4.COCCC
6.0COCC
8.COOCC
10.0CCC
12.0CJO
14.0000
16.COOC
18.0CGC
20.00CC
22.COOO
24.0COC
26.0COC
28.PCCC
30.00CO
32.0COO
34.00CC
36.000C
38.0000
40.0COO
42.0000
44.00CC
46.000C
48.00CC
50.00CC
52.00CO
54.0COO
2.00000:
6.C0001:
10.0001:
14.0001:
18.0001:
22.0001:
26.0001:
30.0001:
34.0001:
38.0001:
42.0001:
46.0001:
50.0001:
54.0001:
53.0001:
62.0001:
66.0001:
70.0001:
74.0001:
73.0001:
82.0001:
6.00000
10.0000
14.0000
18.0000
22.0000
26.0000
30.0000
34.0000
38.0000
42.0000
46.0000
50.0000
54.0300
58.0000
62.0000
66.0000
70.0000
74.0000
78.0000
82.0000
86.0000
00
TABLE 16 (CONTINUED)
1
ii)?UD_J
IBDJLA.I
34
5
6
7
8
9
1C
11
12
13
14
15
16
17la
19
20
21
22
23
24
25
26
1
1 2 3456 .L
197 123
120 515 . 19
87 224 268 152 78 13
51 163 841 1100 406 223 64
62 454 25 18 150 146 304
71 245 2296 1C8 1046
271
180 1476.
.
.
?
?
?
?
?
*
?
9
?
?
?
^1__22_1 *__ *_ _
.
95
4
22 . -
.10 11 12 L3 14 15 16 II IS IS 2Q 21_i__
0
49 I 6
1
(
6
?
?
?
?
L3
)9
?2
?
*23
9
2 39
*
*
?
?
?
?
*
*
?
?
?
8
3
2 5
,
TABLE 17
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY EQUALDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THF SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
CIV. RANGE OF QBAV
M/SQ.CM
RANGE OF XBO
1
2
3
4
56
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
2223
24
2526
27
2829
30
31
3233
3435
3637
0.0 : 50.0000
50.0001:
100.
15C.
200.250.
300.
350.
400.
450.
500.
550.
6CO.
650.
700.
750.
001:OCl:
001:001:
001:
001:
001:
001:
001:
001:
001:
001:
001:
001:
800.001:
850.
900.
950.
1000
1050
1100
001:
001:
001:
.01:
.01:
.01:
1150.01:
1200
1250
1300
1350
1400
1450
1500
1550
1600
16501700
1750
1800
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
.01:
100.
150.
200.
250.300.
350.
400.
450.
500.
550.
600.
650.
700.
750.
800.
850.
VOO.
950.
1000
1050
1100
1150
1200
1250
1300
1350
1400
1450
1500
1550
1600
1650
17001750
1800
1850
000
CCOCOO
OCCOCC
OOC
OCC000
OCC
ooc
CCO
CCOcoo
ccc
CCO000
ccc000
.00
.oc.oc
.oc.oc
.oc
.00.CO
.oc.oc
.oc
.oc
.00.oc
.00
.00
.00.00
-0.
-0.
-0.
-0.
-0.0.
0.
0.0.
0.
0.0.
0.
0.
0.
50000: -0
39999:-0
29999:-0
.40000
.30000
.20000
19999:-0.100CO
09999:-00000 l:
10001:
2C001:
30001:
40001:
50001:
60001:
70001:
80001:
90001:
0
00
0
0
00
00
1
.00000
.10000
.20000
.30000
.40000
.50000
.60000
.70000
.80000
.90000
.00000
CIV.
38
39
40
41
42
43
44
45
RANGE OP QBAV
W/SO.CM
1650.01:
1900.01:
1950.01:
2000.01:
2050.01:
2100.01:
2150.01:
2200.01:
1900.00
1950.00
2000.00
2050.00
2100.00
2150.00
2200.00
2250.00
00cn
TABLE 17 (CONTINUED)
?BD_.
12
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
I'-i
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
A5_J
1L
.1 _
2
3
?
22
2
31
12
2
*2
31
^.. ^,_ ,3., 4 .? ,5
2 5 11 25
1 6 18 377 11 41 71 1
7 13 52 127 3
5 25 53 124 36 25 35 114 11
7 16 30 66 <5 9 13 25 '
4 6 10 372 . 17 33
5 6 5 2J
3 2 5 323 11 10
1 9 101 4 11
1 2 2 261 4 30
2 1 4 1013 17
54 177 3
0 15
7 55 1
6 24 1
1
1 3 11 1
1
3 2
1
6
1
1
11
11 1
1 3
2
1 2
? 0
? *. .
, _ . l_
.6
30?9 1.
itt 4
25 4L7 2
36 1
33 l
?5
36
16
2
Jt
3437 5
55 <9
L2 4
75 2
34
S.6
27
L7
8
_J
72 1
11 7
51 7<
97 2<
22
50
7
.a
18 2
76 7<
?9 4
i6
J8
7
IQ
71 3
JO 5
37 1'
36
1
U
LO 21
21 3<
?4 <
4
12
33 2<
S9
iO
7
13
E?3 1<37
22
i>6
1
2
15_.
SO
1
,1
1L_
L
00
TABLE 18
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILE
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
CIV.
I
2
3
^5
6
7
3
9
10
1 1
1 fi_J I_
1 B_J1
2
3
4
5
6
7
a
655
275
60
4
40
70
54
53L j.
RANGE OF P
MPA
0.0 : 3.C35CO
3.03501: 4.995CC
4.99501: 5.8580C
5.85801: 6.80620
6.80621: 6.926CO
6.92601: 8.376CC
8.37601: 13.6999
13.7000: 17.040C
2 2 *_
116
278
186
20
151
162
190
141
12
183
89
130
437
174
76
141
131
138
242
42
219
162
258
83
RANGE OF G
G/S.SOCM
0.0 : 30.3500
30.3501: 58.5009
58.5001: 70.3100
70.3101: 101.970
101.971: 135.210
135.211: 140.700
140.701: 202.300
202.301: 237.320
237.321: 337.600
337.601: 1557.00
5 S> 1 fl.
42
175
324
85
243
190
70
98
11
192
92
171
364
179
91
170
83
99
167
76
286
172
216
145
1
134
244
147
189
149
212
174
1
3 1Q_I
67
65
116
155
223
196
159
267
415
3
36
59
99
152
185
298
0000
TABLE 19
DISTRIBUTION OF TESfS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF OBG
W/SO.CM
RANGE OF G
G/S.SQCM
1
2
3
4
5
6
7a
9
10
1 I
1 car" i ~~~ ~~i? WnL .
2
3
4
5
6
7
8
9
10
574
180
28
161
41
75
30
74
41
47
C.O :
44.7501:
71.1561:
88.9601:
1C6.321:
125.373:
149.841:
177.632:
215.801:
2S7.201:
44.7500
71.1560
88.9600
106.320
125.372
149.840
177.631
215. 80C
297.200
2221.00
2 3 A_
260
2C8
127
171
141
112
86
49
22
58
82
188
354
112
89
144
147
103
24
4
73
166
11V
113
123
143
153
156
104
95
O.C : 3C.3500
30.3501: 58.5000
58.5001: 70.3100
70.3101: 101.970
101.971: 135.210
135.211: 140.700
140.701: 202.300
202.301: 237.320
237.321: 337.600
337.601: 1557.00
5 6 1 S 3 10_
83
175
161
145
109
97
123
135
123
76
73
97
160
217
253
116
94
132
110
18
37
70
149
107
102
87
137
191
249
115
30
81
97
130
229
207
141
111
132
92
26
62
40
72
123
218
212
171
184
140
9
21
12
19
38
48
124
128
246
602
0010
TABLE 20
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILE
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
DIV. RANGE OF XBC RANGE OF
G/S.SUCM
1
2
3
4
5
6
7a
9
10
i 1i __?_! -1 -
1 HL-.I
2
3
4
5
6
7
8
9
10
I
21
19
38
73
62
50
82
198
301
407
,
-C.50000:-0. 03820
-0.03819: 0.08035
C. 08036: 0.168S7
0.16898: 0.22790
0.22791: 0.28198
C. 23199: 0.3409C
0.34091: 0.40477
0.40478: 0.48075
C. 48076: 0.60150
C. 60151: 1.00000
2 3 ft .
34
37
51
32
40
64
118
168
2?5
365
20
32
39
62
86
122
193
224
186
283
80
75
129
89
159
138
164
110
217
84
0.0 : 30.3500
30.3501: 58.5000
58.5001: 70.3100
70.3101: 101.970
101.971: 135.210
135.211: 140.700
140.701: 202.300
202.301: 237.320
237.321: 337.600
337.601: 1557.00
5 b 7 fl 9 _
30
75
118
109
149
201
174
166
155
50
53
89
150
114
114
168
243
269
50
20
129
217
201
158
134
94
173
87
34
17
140
145
140
132
254
322
87
21
8
1
157
254
210
319
231
60
11
4
2
?
. 13
583
305
171
159
19
8
2
.
.
?
10o
TABLE 21
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12*73
T>F SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF XIN RANGE OF G
G/S.SQCM
12
34
56
78
910
G_,
1-JLLft-J1
2
3
4
5
6
7
8
9
10
1_
80
177
177
111
86
39
45
221
276
39
-1.-0.
-0.-C.
-0.-0.
-0.-c.
-0.-0.
2_
231
137
172
146
135
75
99
67
110
72
10000:-0. 37750
37749:-0. 2593025929:-0. 19883
19882:-0. 1621516214:-0. 13153
13152:-0. 0991009909:-0. 06329
068?8:-0. 04037040 36: -0.0 I CCO
00999: 0.900GC
3_
159
133
123
156
129
135
127
97
118
70
4
127
137
100
115
87
75
114
95
147
248
0.0 : 30.350030.3501: 58.5000
58.5001: 7G.310070.3101: 101.970
101.971: 135.210135.211: 140.700
140.701: 202.300202.301: 237.320
237.32U 337. 600337.601: 1557.03
5 fi 2 fl a JQ_
16
56
106
109
120
130
146
94
142
248
138
102
94
132
153
187
148
123
99
94
141
113
101
83
100
124
137
123
125
197
119
94
87
105
105
190
167
145
84
154
120
125
107
88
118
133
174
191
104
88
56
174
180
202
215
15V
90
91
45
35
TABLE 22
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THP TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF HEOO
MM
RANGE OF
G/S.SQCM
1
2
3
4
5
6
7
3
9
10
I
J_^_C_JIhJdfl-J
1
2
3
4
5
6
7
8
9
10
2.70000:
7.60001:
9.35001:
10.1001:
12.2501:
13.4201:
13.8001:
17.2001:
19.0001:
25.6001:
7.60000
9.35000
10.1COO
12.2500
13.42CC
13.8000
17.2000
19.0000
25.60CC
86.00CO
^?^ .2 34
I
480
25
124
.
1
36
118
129
78
260
S3
122
210
?3
14
79
189
139
174
171
66
211
22
62
199
163
45
197
204
78
90
62
207
111
106
78
149
144
188
110
0.0 : 30.3500
30.3501: 58.5000
58.5001: 70.3100
70.3101: 101.970
101.971: 135.210
135.211: 140.700
140.701: 202.300
202.301: 237.320
237.321: 337.600
337.601: 1557.00
5_, 6 1 _fl S 13
49
132
233
222
57
70
89
115
168
92
82
235
50
118
215
222
47
113
173
15
90
121
160
113
123
44
160
158
146
129
81
122
132
236
213
2C5
80
50
79
52
93
134
56
235
177
269
183
49
21
31
112
97
14
91
28
176
243
155
43
233
10ro
TABLE 23
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
DIV. RANGE OF XBC RANGE OF OBAV
rt/SO.CM
1
2
3
4
5
6
7
3
9
10
1 1
i
2
3
4
5
6
7
8
9
10
22
32
25
19
25
32
54
125
291
621
-0.50000:-0. 03820
-C. 03819: O.C8035
C.OdC36: 0.16897
0.1&89d: 3.22790
0.22791: 0.28198
C. 28199: 0.34090
C. 34091: 0.40477
C. 40478: 0.48075
0.48076: 0.60150
0.60151: l.OOGCO
2 3 &_.
21
18
25
49
74
?5
128
239
366
244
12
22
31
55
83
129
225
207
252
231
20
59
39
93
129
2C9
227
257
147
68
O.C : 41.7500
41.7501: 65.4750
65.4751: 81.8300
81.8301: 100.520
100.521: 117.950
117.951: 136.840
136.841: 166.247
166.248: 203.090
203.091: 277.200
277.201: 2221.00
5 6_
28
42
75
118
170
200
271
191
97
55
43
58
100
239
255
254
132
95
51
20
2 6 3 1Q.
52
119
251
232
166
151
121
107
38
8
118
248
238
177
216
133
82
26
6
?
206 725
375 275
267 196
230 35
117 13
46 t
7
?
* *
?
(A)
TABLE 24
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILE
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THF SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE'
01V. RANGE OF BC
X100G
RANGE OF XBO
1
2
3
4
56
7
8
9
10
0.3 :
0.26001:
C. 35401:
0.44526:
0.54641:
0.68061:
C. 84061:
1.06751:
1.41601:
2.29601:
0.26GOO
0.35400
0.44525
0.5464C
0.63060
0.84060
1.06750
1.41600
2.296CO
17.2000
-0.50000:-0. 03820
-0.03819: 0.08035
0.08036: 0.168S7
0.16898: 0.22790
0.22791: 0.28198
0.28199: 0.34090
0.34091: 0.40477
0.40478: 0.48075
0.48C76: 0.60150
0.60151: 1.00000 <?>
1 1
i-JSBD-i J 2 3. 4_.1 BC
1
2
3
4
5
6
7
8
9
10
1
53
80
110
184
138
140
167
151
109
115
41
72
94
14d
157
155
181
141
124
55
69
72
120
141
129
155
191
136
153
81
230
207
49
100
102
91
129
119
85
95
5 ft 1_.
172 177 141
260
95
55
86
116
145
137
109
73
169
226
76
64
97
115
129
123
71
121
185
148
87
91
101
150
136
87
a a_.
138 113
67
124
217
61
92
90
135
119
204
123
110
99
129
62
74
64
194
280
1Q_
113
77
94
79
255
208
54
85
96
Id6
TABLE 25
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILE
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 12473
ThE SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF 80
X10CO
RANGE OF L/0
1
2
3
4
5
6
7
8
9
10
1 1
l__fl?_J1
2
3
4
5
6
7
8
9
10
I 41
66
69
120
65
63
139
153
2o5
404
C
0
0
C
0
C
C
1
1
2
.0 :
.26001:
.35401:
.44526:
.54641:
.66061:
.84061:
.06751:
.41601:
.29601:
0
0
0
0
0
0
1
1
2
?
?
?
?
?
*
?
?
?
17
26000
35400
44525
5464C
6806C
8406C
06750
4160C
2960C
.20CC
2.00000: 31.
31.6001
50.0001
94.5001
118.
146.
196.
271.
310.
001
001
: 58.: 94.
: 118: 146
: 196
001: 271
001: 310001: 767
2 3456
35
2G
42
53
56
91
S6
138
145
6t5
115
42
4V
60
90
137
207
223
288
130
13
38
55
27
19
94
70 202
108
173
245
258
277 285
361 200
336
34
141
10
19
92
148
1V2
237
217
193
141
70
4
6000
0000
50CO
.000
.000
.000
.000
.000
.000
11 a 9 I
215
353
222
164
161
93
45
31
3
^
68 714
209 409
348 220
305 81
200 d6
182 13
3 2
?
-. .
10en
TABLE 26
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILE
DIVISIONS OF THE RANGES OF 2 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV. RANGE OF BC
X1000
RANGE OF HE
1
2
3
4
5
6
7
89
10
1 1
I aft i1
2
3
4
5
6
7
8
9
10
10
20
19
15
51
44
31
53
10 a
891
0.0 : 0.260CC 0.0 : 628.300
0.26001: 0.35400 628.301: 1721.00
0.35401: 0.44525 1721.01: 3373. CO
0.44526: 0.54640 3373.01: 4764.20
0.54641: 0.6BC60 4764.21: 6296.50
0.68061: 0.84060 6296.51: 8990.00
0.84061: 1.06750 8990.01: 12360.0
1.06751: 1.41600 12360.1: 16099.0
1.41601: 2.2960C 16099.1: 25660.0
2.29601: 17.2000 25660.1: 179000.
__2 3 ^ 5 b
56
24
21
33
96
69
1C6
140
3S7
304
59
17
40
50
119
123
164
243
392
40
48
24
71
120
131
147
182
332
187
5
92
82
127
106
206
258
130
175
69
3
93
137
146
109
110
156
257
177
59
3
i a a ia_
154
178
1U9
123
149
167
188
65
33
1
220
195
180
345
110
96
74
26
1
?
263
223
267
181
124
90
76
22
2
?
252
348
187
165
150
97
39
9
.
*
to
97
NOTE
As Tables 27 to 29 each occupy two pages and are to be read in conjunction,the first of these commences on page 98.
TABLE 27
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 4 VARIABLES CONSIDERED SIMULTANEOUSLY
OIV.
1
2
3
4
5
67
6
THE TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES CF THE VARIABLES At.
RANGE CF XIN
-l.lOOOOt-C.25930
-0.25929J-0.16215
-0.16214:-O.C9?10
-C.099C9:-O.C4037
-0.04C36: C.90COO
RANGE OF G
G/S.SQCH
C.O : 58.5000
58.5001: 101.970
101.971.: 140.700
140.701: 237.320
237.32U 1557.OC
THEIR RANGE DIVISIONS ARE:
RANGE OF P RANGE OF HEQO
HP A MM
0.0 :
3.03501:
4.99501:
5.85801:
6.80621:
6.92601:
8.37601:
13.7000:
3.03500
4.99500
5.85800
6.80620
6.92600
8.37600
13.6999
17.0400
2.70000: 9.35000
9.35001: 12.2500
12.2501:
13.8001:
19.0001:
13.8000
19.0000
86.0000
TABLE 27 (CONTINUED)
1~ 11 2
1 3
I 4
l^ ,^5^.
2 I2 2
2 37 4
2_ 5_3 j
* 2
"? 3
3 4
3__ 5_
4 1
4 2
4 3
4 A
_4 , 5 J
5 i
5 2
5 3
5 4___5 5_J
6 1
6 2
6 3
6 A
__6 S_J7 1
7 2
7 3
7 4
2__ 5_J
8 1
8 2a 3
8 4
1 8 5_J
I _2 _3_ A 5_J
I 361..
2 3 ...
4 ...
202 2 I . 1
L_222 i J 2 . J
14 8 14 8 .
12 17 43 26 1
4 7 20 49 1
L 3?34?23 22_ 3_J
5 a 8 4 1
3758
4 4 10 8 6
L 3 11 22 22 13_J
. . 1 . .
4 .
. . 644
5 10 3
L ... A 1 3 lfl_J
8 14 7 12 13
3 11 15 9 10
i 8 7 11 8
5 13 8 20 7
3? 2J3? IS 3fl ia_J
32 52 50 17 40
1 6 11 9 26
18 35 42 16 69
3 10 14 6 35
* -12 12 _12 JJLJ
11 13 7 4 5
11 13 14 7 20
31132
3 . 1 .
2 2- _1_ 4 2_J
?3 70 94 45 80
32127
18 19 27 17 24
... 2 ?
L-_ 4 l 3 -
? ? ? ?
_, ,1 2 34 _.?_?.
? ? ? *?p
3 ...
1 ...
27 12 16 2
29 10 23 3
33 12 29 12
|
35 30 40 53 13
31 35 43 74 2o
39 33 48 66 33
I A6__fi?_112_l 3 Z 44_J
. 111.
4 7 12 54
4 4 14 6 10
3 6 9 4 11
| 5 3 ,a A 3_j
6922
5 19 33 41 37
2 9 21 27 27
8 21 17 28
.l-.^-.S^JLfr?^ IJU^
12 4 3 1
5 10 23 32 41
7 4 15 22 37
6 9 28 30 29
_6 13 56 34 16_J
31 13 2 57
10 8 . 96
44183
36233??? ^_J &? a . J
76252
65131
21. 3 .
1121
2 - 2 2 -
^1_^ 2 .3,-._4^ _5^
? ? ? ? ?
4 . 21
184. 1
U_5 _1$_,,^ ,12 _5_
. . 3 . .
14 4 .
24 41 23 .
28 38 43 49
L A 3 lfl_ 4 J_j
....
. 1 ...
7 3 .
4314
L *_ * _i__* 3-J
3 5 ...
1 35 31 8 .
. 44 63 57 20
43 57 75 122
I 1 11 11- 13 25-J
1231.
4 56 26 10 2
1 48 45 43 30
2 46 42 54 86
I _2 LZ Id 12 ia_J1 .
2 .221
1 . 234
L 16 31 22?15 21_J
11 23 11 48 13
i 2 8 IB 23
3 3 6 4 Id
4 4 4 9 20
2 14 2 9 5
36 30 54 62 51
12 9 15 18 45
7 10 8 12 22
10 10 10 15 33
_ . . . - .
I 1 _2 3 4 5.J
12 . . 1 16
73 . . . 71
30 3 12 12 382 5 16 11 18
12 AJL ? _ 34 24 J
76 ....
78 16 1 . 1
18554
24..
* 4 2 4 2 J
13 14 4 . .
6 12 7 .
4 8 14 .
4 3 12 1 1
L _2 ? S - ? J
21..
11..
.. 1 JL_ 1 2_J
21 44 18 3 .
15 44 50 13 1
12 18 29 16 4
17 37 39 36 7
L 4__22? 3fl 13 4_J
38 20 2 20 2
24 15 5 20 2
20 18 6 17 2
27 11 2 18 2
1 1 2 JL .. _?? J
32 46 17 66 47
22 27 17 37 63
6 11 12 17 46
4 14 3 11 19
L 1 5 i 4 1_J
14 40 33 63 144
1 10 3 11 79
3 7 8 13 28
1 2
.? A? .?___.?___ A? ?A? J
5333
L _J 2 3 4 5_
15 .. .2294 4 . . 94
5S . 160
932 1 11
L? 1.3? 12__12? 1 1__-__J
82 15 3 1 .
103 21 13 1 .
28 11 10 .
19 22 10 .
11 2a 33 Ifl * J
28 13 2 . .
692.
1572.
5 10 9 4 .
13 23 4.1 2S * J
. . 1 . .
233.
2298.
385.
L 1_ 2_ 3 4 *? J
26 36 16 1C .
21 38 30 14 .
12 22 27 11 .
13 39 28 22 .
6__52^_50__3? B.J
18 25 15 3 .
3 15 14 3 .
2 10 16 12 .
4 9 14 20 1
__ * 11 11 !__*? J
39 45 7 64 7
12 23 10 28 1'J
10 15 7 31 7
7 12 6 11 8
J _24 _14 IS 2.J5 . 3 31 23
2 . . ? 6 18
2 1 51 1 .
L 3_* 2 1? *? J *??
vo
TABLE 28
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 4 VARIABLES CONSIDERED SIMULTANEOUSLY
DIV.
1
2
34
56
7
8
THF TOTAL NUMBER OF TESTS IS 12473
THE SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
RANGE CF XBO
-0.50CCO:
O.C8C36: C.C8035C.22790
0.22791: C.34090
C.34C91: G.48C75
C.48C76: l.COOOO
RANGE OF G
G/S.S3CM
0.0 : 58.50CC
58.5001: 101.970
101.971: 140.700
140.701: 237.320
227.321: 1557.00
RANGE OF
MPA
0.0 :
3.03501:
4.99501:
5.85801:
6.80621:
6.92601:
8.37601:
13.7000:
3.03500
4.99500
5.85800
6.80620
6.92600
8.37600
13.6999
17.0400
RANGE OF HEQD
MM
2.70000: 9.35000
9.35001: 12.2500
12.2501: 13.8000
13.8001: 19.0000
19.0001: 86.0000
Oo
TABLE 28 (CONTINUED)
1
1 HEOD
1
1 E_
j ? JCBC
"l 1
1 2
1 3
1 4
i.__l 5_
? 1
? 2
2 3
2 4
2 5_3 1
T 2
H 3
3 4
3 5_4 1
4 2
4 3
4 4
__-.4 5_
?5 I
5 2
5 3
5 4
5 5_A I
6 2
6 3
6 4
6 5_7 1
7 2
7 3
7 4
7 51
ft 1
A 2
8 38 f>
1 ._fl. 5...I
11111
___J 2_ 3_ 4 5_J
L
1 7 ...
6121
168 1 2 . .
310 2 ? n
1 . 2
1183
2 38 80 .
33__6J__.60 24 ?_-J
? ? ? ? 1
2 3 16
2 b 14 11
6 17 18 .
? 12__23__22 4 . ? 1
2
2 . 13
. 5 20 2
e 5 6 24
2 9 13 32 20
24 12 25 11
4 24 13 24 1
__15__11? 13 3?..? J14 27 13 Gl
lo 33 20 89
4 22 36 15 17
11 31 21 11 2
~. 5? 6 8 Is"
2 7 10 9 11
68523
942..
1 29 75 45 95
7 27 36 19 13
12 21 11 4 318 12 1 1 .
4.6.,, 6 -,, . ,????-,
22222
1 ^_2 3 ^_* 5^,
* ? ? ?
? ? ? ?
ft
* ? ? ?
9 .
22 8 .
3 25 62 13 .
_1-L2 22- ft A A J
34 66
42 187 46
47 132 99 4
_15J_13J ZQ__lfl__A__J.....
2 21
15 5 5
5 26 13 2
| JL? ifi 3_ A _ A J
3 19
8 7 21 7d
19 48 68 8
24 42 .
? ^ 3_A * J
11. 3
3 7 24 105
9 46 87 15
32 47 4 1
l_24 3__25 ft ?__J29 11 3 14 16
9 8 1 16 3
6843.
835..
4 ~. ~*6~~*6?*2~54. 12
4 . 2 .
8 5 ...
3 3 J 3 3
L _, ul , 2 3 4_,._5_
22
1 13 . 12 5
3 10 1 .
2 . 7 .
4 .
1 1 1 16
7 61 40
78 8 .
L A _I4 ft M. A.
? ? ? ? O
141
10 .
A 5 ? * * J
5 82
14 118 85
3 150 36 .
5-135 _4_ M -A J
1
2 13 86
8 13 86 50
27 119 26 .
3 10 20
14 7 4
29732
15 22 5 * - J22 5 49 27
4 10 1^ 33 52
1 4 13 6 .
191..16 1 ^
 M J1 5 39 59
11 59 64 92
4 28 23 4 .
29 19 .
.,.3.2., ... ... ,. ...,? J
44444
1 2 3 4 5_
1 . 4 23 148
8 24 24 35 19
21 31 .
41 ....
L 5JJ * * jt *
1 . 26
3561
12 4 5 1 .
41 20 2 .
L-1Q2 2 * * .
1 12 1 1
12 29 .
2 28 5 .
L 21 3 * A &
1 2
1 .
? ? 2 ? ?^ 4
 x _.. ?,
2 16 3
8 51 36 13
38 91 27 .
2 104 22 2 .
61 2fl ? *_ A_3 . 10 6
5 2 37 i
1 23 9 25 .
17 33 4 3 .
32 2 ? M _*.1 27 15 93 162
4 40 32 40 14
23 24 3 2 .
25 12 .
12 A * A m12 26 64 237
22 16 24 16
1 16 2 .
5 6 ...
L_12 1__^ _.. *_J
55555
1 2 3 4 5-
14 . 23 287
68 9 10 5 .
60 5 2 .
35 5 .
12 * A J? A j2272.
62 18 21 6 .
60 33 27 4 .
72 40 5 .
45 * 9 * A J2155.
1 2 14 12 .
1 30 24 14 .
21 26 12 5 .
22 d 13 1 A J8 14 .
. . 10 6 .
. 76..? z ? ? ?
6 9 .
23 56 56 1
5 56 67 12 2
32 86 12 2 3
_41 H_ IQ fl 2_J
3 1 1J 25 I
3 14 35 17 .
36 21 3 .
8 25 1 .
13 A A _A A _J47 71 14 142 40
14 21 16 11 1
3 11 6 .
2 16 2 .
4 A 4 A A J7 . 8 40 44
3 ... 2
__
TABLE 29
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 4 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THF SYMBOLIC NAMES OF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
01V. RANGE CF CBAV RANGE OF G RANGE OF P RANGE OF HE00
h/SO.CM G/S.SCO MPA MM
1 0.0 : 65.4750 0.0 : 58.5000 0.0 : 3.03500 2.70003: 9.35003
2 65.4751: IOC.520 58.5001: 101.97C 3.03501: 4.99500 9.35001: 12.2500
3 ICC.521: 136.840 101.971: 140.700 4.99501: 5.85800 12.2501: 13.8000
4 136.641: 203.090 140.701: 237.320 5.85801: 6.80620 13.8301: 19.0000
5 203.091: 2221.00 237.321: 1557.03 6.80621: 6.92600 19.0301: 86.0000
6 6.92601: 8.37600
7 8.37601: 13.69998 13.7000: 17.C400
Oro
roo
VI 11 *? z ...
r~5E?30T~Tz ? TV ? 9r ?
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1
p-g- ^ ^ .^^^^^^
r T ? ^B ? Tv e
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8n ? L?
V i
? i
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I i
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E 9
Z 9
I 9r~ff s"
V <*
? 6
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I S[?5 9
V V
? V
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1?5- ?
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Tm-a ?-g- ?
((13nNIiNOO) 63 319V1
TABLE 30
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 4 VARIABLES CONSIDERED SIMULTANEOUSLY
THE TOTAL NUMBER OF TESTS IS 12473
THF SYMBOLIC NAMES CF THE VARIABLES AND THEIR RANGE DIVISIONS ARE:
OIV.
i2
34
5
RANGE CF BO
X10CC
0.0 : 0.35400
0.35401: 0.54640
3.54*41: 0.84060
C.84061: 1.41600
1.416C1: 17.2COO
RANGE OF ME
C.O : 1721.00
1721.01: 4764.20
4764.21: 8990.00
8990.01: 16099.C
16099.1: 17900C.
RANGE OF LFR
0.0 : 6.35000
6.35001: 21.7500
21.7501: 55.2700
55.2701: 150.100
150.101: 3036.00
RANGE OF XBO
-0.50000: 0.08035
0.08036: 0.22790
0.22791: 0.34090
0.34091: 0.48075
0.43076: 1.00000
ACC
*?_J
I 1~
1 2I 3
1 4
1- 5 J? 1
7 2
? 3? 4
2. i_J
?? 1
3 2
3 3
3 4
3 _5 J4 I
4 2
4 3
4 4
ft 5_J
5 1
5 2
5 3
5 4
L 5 5_J
11111
L 1 2 J A 5_jL
5 . . .
5 ? . .
3 . . .
2 . .
| 23 1 1 ? _. _^
.1 . .
3 .
41 . .
24 2 1 26 14
L _56 12 _25_ 2 _^ _.
11 2 ...
3 2 ...
12 10 2 .
18 39 24 3 .
51 2^ 2 1 ,
22 3 15 2 1
3 V 15 9 7
14 60 40 44 19
14 103 97 68 3
L __1 A3 3.2- 1 . _J
6 3C 16 45 87
44 29 133 274
2 69 36 74 280
2 31 26 41 97
. _* _5 ifl 1 2_J
J 2 3 ft 5_J
2 1 ...
2 . 1 .
1241.
L_lfij: _2fl _5 + * J
2 ... 1
2 . . 37
86371
34 45 33 2 1
6 . 4 .
4 6 3 13
4 19 39 44 6
6 63 158 72 12
| J?_ 32_ 2_ - . J
2 54 8 72
10 29 69 56
23 24 110 76
22 56 36 13
L -- _4 JL. - ,? -^J
1 9 8 160 293
2 d 72 163
1 6 20 20 58
14621
L 1 2 3. A 5_
.....
1 . . 2 .
3 . 2 11 1
2 32 11 1 .^146 , 40 ,.
1 ...
1 . 23
9 18 25 11 2
11 99 133 d .
7 . 13 7 2
9 27 92 13
26 78 76 10
13 62 41 40 3
2 68 72 399
5 61 26 173
6 35 27 5
14 15 .L . * _?.
 A A J8 13 100 86
1 34 2
1269.
1 .
L ? ,. ?? * _-^^J
1 2 3 A 5_
2 5 34 17
34 54 40 1
_3.5J fil A *
6 . ? .
6 27 8 10
2 96 35 31
4 234 64 6
IS-lflZ 2 _.. __..__
3 3 44 178 8
1 10 125 357 70
1 29 49 14 1
5 20 8 . 2
46 61 71
36 4 Id
2 12 .
4
3 19 11 4
1 . 1
1 .
L I_ I _I
c e c c c
^ 2 3 A 5_
14 I 2 . .
47 35 6 .
193 56 14 . .
155 60 10 .
-6B2 5A_ 1 * Ji14 49 45 14 .
8 121 94 IS .
I 73 271 27 .
7 2J a .
2 2 * A _*__
5 12 101 f2 19
6 2 40 . 1
2 12 4 .
2 4 ...
4 lo 3 16 2V
2 5 .
1 .
2314
? ? ? *
* ? * *
? ? * ?
__
TABLE 31
DISTRIBUTION OF TESTS AMONG REGIONS DEFINED BY PERCENTILEDIVISIONS OF THE RANGES OF 4 VARIABLES CONSIDERED SIMULTANEOUSLY
THF TOTAL NUMBER OF TESTS IS 10803
THE SYMBOLIC NAMES CF THE VARIABLES ANO THEIR RANGE DIVISIONS ARE:
OIV.
1
2
3
A
5
RANGE CF PP/0 RANGE OF L/0 RANGE OF ROIA
MM
RANGE OF RODS
1.00000:
1.C8501:
1.19CC1:
1.312C1:
1.356C1:
1
1
1
1
2
.C6500
. 19000
.21200
.35600
.23000
0.0 :
62.0001:
11A.001:
155.001:
272.001:
62.COOO
HA.
155.
272.
730.
COOoco
oco
000
0.0 :
10.
10.
1A.
15.
1001:
8001:
4001:
9501:
10.
10.
1A.
15.
21.
1000
8000
AOOO
9500
0000
2.00003:
7.00001:
16.0001:
20.0001:
7.00COO
16.0000
20.0000
37.0000
1
1 120_r i
l 2
I 31 A
_. 1 5_J
7 1
2 2
7 3
7 Ai ;> 5 j
3 1
?>> 2
3 3
J A
3 5 JA 1
A 2
A 3
A A
4 5 J5 1
5 2
5 3
5 A
i 5__ 5_J
ill!
1 2 3- 4 5_JL
12 ....157 Al
80 15A3 217
? * ? ? ?
161
63
68 ? ? * *4y J19 .
? * ? ? ?
A73 3 5 .
16 A7
? ? ? ? ?1?J4 102 ^ 15 , ,
? * ? ? ?
? ? * * ?
* ? *_ * 1 I
271
? ? ? ? ?
? ? ? ? *
I J
2 9999
L _ 1 2 3_4_ _5_J
? * ? *
? ? ? ?
? ? ? ?
21 1_ _I _. ..
? ? ? ?
2
181 318 825 I
1 ^ .. ? _? .. 1
51
338 9A 130
A7
_143 53 * . .. _J
332 A3 168
35 IA
? * ? * ? ?
? ? ? ? ?
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? ? ? ? ?
3 0 ?? ?% a
L 1 2 3 4 5_
.....11A
? * ? ? *
? .. 461 54 * J
? ? * ? ?
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? ? * ? ?
58 17 AA
? * ? ? ?
103?.. ^
 A .. * J75 . 73
5A 1AA . 36
? ? ? ? ?
? ? ? ? ?
... * _ ^ __*_ J
12 73 . 106 1190
? ? ? ? ?
? ? ? ? ?
? ? ? ? ?L + -. ^ * _2a.j
i i 3
* ?*
L . .?
\ 119 ISA
? * ?
21
? * *
1 I 146
* * ?
? ? ? 6*
? * ?
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i
.4 5_
*
6
*
A
?
?
1
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1__
*5 723
)6
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t ?_ J265
> ?
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_ _
CDcn
'-h ft"? I J G u -r?s
. G ?SC r-|nfl
2-5*10
icr
*~^9cc
LU
z 2-0
i? 4
Xt
l~?a
t? ?i
* 15a:
CO
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? 1.0
CO
LU
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cc 0-5
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z
0,0
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-
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r
X
r- - ' - - -
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-
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^
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1 -
hi ^1 [ JA _^ , r^ :
80 irj 0 16 0?-/ r *./ * C_ - ?*/ i '^J a *J
o-J
VSTEH PRESSURE
FIGURE 1. DISTRIBUTION OF TESTS OVER THE RANGE OF SYSTEM PRESSURE
TSc"? n"r 12163
Firs*- *c ?h'rd
?h* "^-^c- 0.0 U- BOG. 0 g.s- 1 .c*-2
u"* o4 57 C4 , I"f3.3. ZCs.B g.?-Lc.
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0,0 -:1J(), ij
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f50'X 0 500, 0
FIGURE 2. DISTRIBUTION OF TESTS OVER THE RANGE OF COOLANT MASS FLUX
c fi r, f:OUO, U
CL
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V --?
IT
2 ^00.0?7
oren
^ 300, 0
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COOLRNT OUflLiTY qj CMRNNEL INLET
FIGURE 3. DISTRIBUTION OF TESTS OVER THE RANGE OF COOLANT QUALITY AT CHANNEL INLET
to
M's'-ogr-asi ha" wid*-h -
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i 1*5 0-6 U? 0 1.2=
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-0,5 -0.? -0,0 0,? 0,5 0,?
COGLPNT Dijl.K QU?L!TV RT BURNOUT
FIGURE 4. DISTRIBUTION OF TESTS OVER THE RANGE OF COOLANT BULK QUALITY AT BURNOUT
500,0
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LOCRL BURNOUT MrflT ^LUX U,c?f
1-0
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FIGURE 5. DISTRIBUTION OF TESTS OVER THE RANGE OF LOCAL BURNOUT HEAT FLUX
L.
Pi*"* o?a JdVl tszH. in *h* ^digc 3.ICCG ft? "57.10
Fir";*- t-o *h'rd quo"-'-'i ei o"6 u* <* 9^5. 3.0^2. 19.03
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f i
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0,0 10. 0 20,0
NUMBER OF ROD:
30,0 i*0.0
FIGURE 6. DISTRIBUTION OF TESTS OVER THE RANGE OF NUMBER OF RODS
U'-r l^H-H.7 ?rS*-?
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d "
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0 25, 0
co
FIGURE 7. DISTRIBUTION OF TESTS OVER THE RANGE OF ROD DIAMETER
FIGURE 8. DISTRIBUTION OF TESTS OVER THE RANGE OF ROD PITCH:DIAMETER RATIO
FIGURE 9. DISTRIBUTION OF TESTS OVER THE RANGE OF HYDRAULIC EQUIVALENT DIAMETER
NUMBER OF TESTS IN BflR WIDTH INTERVflL _
FIGUR
E 10
. DISTRIBUTIO
N O
F TEST
S OVE
R TH
E RANG
E O
F HEATE
D EQUIVALEN
T DIAMETE
R
FIGURE 11. DISTRIBUTION OF TESTS OVER THE RANGE OF HEATED:WETTED PERIMETER RATIO
FIGURE 12. DISTRIBUTION OF TESTS OVER THE RANGE OF HEAT FLUX TRANSVERSE FORM FACTOR
FIGURE 13. DISTRIBUTION OF TESTS OVER THE RANGE OF HEAT FLUX AXIAL FORM FACTOR
roo
FIGURE 14. DISTRIBUTION OF TESTS OVER THE RANGE OF HEATED LENGTH
FIGURE 15. DISTRIBUTION OF TESTS OVER THE RATIO OF HEATED LENGTH TO
HEATED EQUIVALENT DIAMETER
FIGURE 16. DISTRIBUTION OF TESTS OVER THE RANGE OF BOILING LENGTH
FIGURE 17. DISTRIBUTION OF TESTS OVER THE RATIO OF BOILING LENGTH TO
HEATED EQUIVALENT DIAMETER
FIGURE 18. DISTRIBUTION OF TESTS OVER THE RANGE OF BOILING NUMBER x 1000
FIGURE 19. DISTRIBUTION OF TESTS OVER THE RANGE OF WEBER NUMBER
FIGURE 20. DISTRIBUTION OF TESTS OVER THE RANGE OF LIQUID FROUDE NUMBER
Printed by the AAEC Research Establishment