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File 629. l 3/Un3as/No. 708 AIR CORPS TECHNICAL REPORT No. 4271
AIR CORPS INFORMATION CIRCULAR
Vol. VIII
PUBLISHED BY THE CHIEF OF THE AIR CORPS, WASHINGTON, D. C.
February I, 1937
AN INVESTIGATION
Part IV-Effect of Variations in the Component Parts of Three
Particular Types of Stiffeners
(AIRCRAFT BRANCH REPORT)
UNITED STATES
Ralph Brown oraugnon
UBRARY
JUN 19 2013
Non·Depoitor~
Auburn University
GOVERNMENT PRINTING OFFICE
WASHINGTON : 1937
No. 708
TABLE OF CONTENTS
Page
Sum1nary __ ____ _______________________ _______ ______________________________________ _______ _ _
Dates and place of t est s ____________ __ ________________________________ _________________________ 1
Object ______________________ ____________ __ _ __ ___ _____________________ _______ ________________ 1
Description ___________ _______ ___ ____ ____________________ ____ ___________ ________ ________ __ ____ J
T est specimens____ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1
Test apparatus___ ________________ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2
])i sc us~on ____________ ____ ____ _ _________________ _ ___ _ ______________________________________ __ 2
Types of failure ______ ___ _______________________ ______ __________ ___ ~ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2
MA and MC series _ ________ _________ ·_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2
Q and Rseries ___ ~-------------------- --- -- - -- -- -- ------ - ------ - ------------------------- 3
(a) Method of presenting data__ _____________ __ ___ ____ ____ ____ __________ _________ ____ __ 3
(b) Effect of reinforcing strips and backplate ____ _____ ___ ____________________ ______ ______ 3
(c) Effect of stiffener depth ____ ________ __ _____________________ ___ _____________________ ._ 3
(d) Effect of stiffener thickness _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3
(e) Effect of corrugation depth_____ ________ __ ______________________________________ ____ 3
Conclusions and recommendations_____ ______ _________________ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3
R eferences ______ _______ ____________ __ ______ _______ ____ ___ ______ _________________________ ____ _ 4
Tables ______ _______ _____ ________ ____ ______________ ___ ______ ___ ______________________________ 4- 10
Illustrations ___ ____________ _________ _______________________ ___ ____ ___________________________ l 1- l 9
LIST OF TABLES
TABLE I. Physical properties of test specimen material.
II. Test data and calculations of MA and MC series.
III. Test data and calculations of MA and MC series.
IV. Test data and calculations of Q series.
V. Test data and calculations of Q series .
VI. T est data and calculations of R series.
VII. T est data and calculations of R series.
LIST OF ILLUSTRATIONS
F1c u RE 1. P ersp ective of t ypical test specimen.
2. Section type used in specimens of M series.
3. Section types used in specimens of Q and R series.
MA AND MC SERIES
4. Average stress versus length-Effect of reinforcement strips-0.010-inch sheet.
5. Average stress versus length- Effect of reinforcement strips- 0.030-inch sheet.
Q AND R SERIES
AVERAGE STRESS CURVES
6. Average stress versus length- Effect of changes in component parts of stiffeners. W = }~-. 0.010- and
0.030-inch sheet.
7. Average stress versus length- Effect of changes in component parts of stiffeners, W = l}h 0.010- and
0.030-inch sheet.
8. Average stress versus length-Effect of stiffener depth.
9. Average stress versus length- Effect of stiffener thickness.
10. Average stress v er s us length- Effect of corrugation depth, W = 7'2- and 1)1,i-in ch, type C stiffeners.
11. Average str ess versus length-Effect of corrugation depth, W = 1-inch , D = 1%-inch , type C and F
stiffen er s .
(II)
STIFFENER STRESS (METHOD A)
12. Stiffener stress versus length- Effect of changes in component parts of stiffe
and 0.030-inch sheet.
13. Stiffener stress versus length- Effect of changes in component parts of stiffener ,
and 0.030-inch sheet.
14. Stiffener stress versus length- Effect of stiffener depth.
15. Stiffener stress Yersus length- Effect of stiffener thickness.
16. Stiffener stress versus length- Effect of corrugation depth, W = %- and 1%-inch, type C stiffeners.
17. Stiffener stress versus length- Effect of corrugation depth, W = 1-inch, D = l Ys-inch, type C and F
stiffeners.
STIFFENER STRESS (METHOD B)
18. Stiffener stress versus length- Effect of changes in component parts of stiffeners, W = }~-, 0.010-
and 0.030-inch sheet.
19. Stiffener stress ver sus length- Effect of changes in component parts of stiffeners, W = 1%-, 0.010-
and 0.030-inch sheet.
20. Stiffener stress versus length- Effect of stiffener depth.
21. Stiffener stress versus length- Effect of stiffener thickness.
22. Stiffener stress versus length- Effect of corrugation depth, W = ?~- and 1%-inch, t ype C stiffeners.
23. Stiffener-stress versus length- Effect of corrugation depth, W = 1-inch, D = l Ys-inch, t ype C and
F stiffeners.
24. Compression test set -up.
25. Specimen MC559 supporting 75,750 pounds, t ype C failure.
(ITI )
AN INVESTIGATION
PROPERTIES OF
COMBINATIONS
OF THE
STAINLESS
COMPRESSIVE STRENGTH
STEEL SHEET~STRINGER
Part IV.-Effect of Variations in the Component Parts of Three Particular Types of Stiffeners
(Prepared by ]. Matulaitis and E. H. Schwartz, Materiel Division, Air Corps, Wright Field,
Dayton, Ohio, Nov. 25, 1936)
SUMMARY
An examination of the test data indicates that-
(1) The addition of reinforcing strips at the welding
flanges of stiffeners can be used on particular stiffeners
to obtain higher failing stresses than those of the original
stiffener. These strips may be used to advantage on
sheet-stringer combinations whose length is such that
the stiffeners fail as long columns. The data in this
report also indicate that the reinforcing strips may be
used in the shorter column lengths to obtain an increase
in failing tress on particular stiffeners.
(2) The backplate or closing strip of the stiffener on
the sheet side is a dependable means, on stiffeners
made up of corrugated sheet, of obtaining an increase
in failing stress.
(3) Increasing the depth of stiffener from 1% to 1%
inches allows failure of stiffener at a lower stress due
to instability of sides. Tests indicate permissibility of
using deeper sections for long columns to obtain
maximum failing stress for this type of stiffener made
up of corrugated sheet without lateral instability of
section as a whole.
(4) On stiffeners 1 inch "·idc aud 1% inches deep a
decrease in stiffener thickness from 0.030 to 0.020 inch
is accompanied by decreasing fai ling stress in the
shorter lengths, but 0.020 inch thickness may be used
to advantage on the longer columns.
(5) Increase in corrugation depth of the component
parts of these stiffeners is accompanied by an increase
in failing stress in depths up to five-sixteenths inch,
which was the maximum depth used in these tests.
Increasing corrugation depth appears to be the most
satisfactory '.method to obtain high failing stresses in
the short length of columns.
(6) The difference in failing stress of comparable
built-up and bent-up sections is small. It is felt that
the buil t-up section is more desirable for use at the
present time due to difficulties encountered in forming
the bent-up sections with the present methods of construction.
DATES AND PLACE OF TESTS
ducted at Wright Field, Dayton, Ohio, using the
equipment of the Materials Branch. Test specimens
which required a load in excess of 100,000 pounds to
cause failure and those whose length was greater than
that which the testing machines at Wright Field would
accommodate were tested at the Bureau of Standards,
Washington, D. C.
OBJECT
The object of these tests was primarily to determine
the effect on failing stress of changes in the component
parts and the most efficient depth to ;-v;dth ratio of
three particular types of stiffeners being considered
for use in a certain design.
DESCRIPTION
TEST SPECIMENS
The specimens were fabricated in accordance with
Materiel Division Drawing S34G494. The material
used in fabricating these specimens was stainless steel
(18- 8) with a proportional limit of 100,000 pounds per
square inch, the proportional limit being defined as the
point on the stress-strain curve at which t he material
has 0.0001-inch unit set.
Three tensile test strips were taken from each thickness
of sheet used and tested at the Materiel Division
in order to obtain the physical properties of the material
used in the specimens. The data from these specimens
are shown in table I.
All specimens were fabricated with electric spot-welds
(minimum weld diameter of seven s ixty-fourths of an
inch), the average spacing of welds along stiffener
flanges being one-fourth of an inch. The welding flanges
were three-sixteenths of an inch wide on all stiffeners,
the minimum width spot-welded through being on
the five thirty-seconds of an inch r einforcing strips.
The tolerance of sheet thickness was plus or minus
0.001 inch per 0.010 inch thickness.
The specimens were straight within one sixty-fo urth
of an inch in 6 inches.
The ends of all specimens were flat within 0.002 inch
and were ground to be parallel to within 0.002 inch per
inch with no indication of burning on the ends.
All tests were conducted between July 1935 and The skin on these specimens was required to be
January 1936. The majority of the tests were con- smooth and free from wrinkles. Absolute flatness of
(1)
2
the skin after welding could not be obtained, the skin
having a slight waviness on the thinner gage. The
amount of waviness was at a practical minimum,
however, and was considered satisfactory.
Warping of specimens at the corners did not exceed
one-sixteenth of an inch.
The test specimens were divided into groups as
follows :
Part M
The purpose of this group was to obtain the effect
on failing stress of adding reinforcing strips at the
stiffener welding flanges. That is, the MA and MC
series consisted of a number of specimens that were
identical to specimens of the same number in the EA
and EC series, respectively, in Air Corps Information
Circular No. 697, except that those in the MA and MC
series had their welding flanges reinforced with 0.030
inch strips, five thirty-seconds of an inch wide.
All specimens of this group shown in figure 1 consisted
of three stiffeners having a pitch of 2 ~ inches. The
stiffeners were built-up sections with reinforcing beads
in the flat sides and back as shown in figure 2.
Part Q
This group showed the effect of changing the component
parts of the stiffeners. Specimens were so
arranged as to show the effect of changing various
component parts of the stiffeners on the failing stress.
This was done for two thicknesses of skin, namely,
0.010 and 0.030 inch, and three lengths of specimen.
The various arrangements of the component parts of
the stiffener section are shown in figure 3.
It is to be noted that this group is divided into two
distinct parts, the distinction in these two parts being
overall depth of stiffeners. Slight changes in length
of specimens will also be observed. These variations
in length are to compensate for the change in value
of the radius of gyration of the section, the specimens
having been drawn up so that the value of L/p remains
constant for each of the three lengths under consideration
of all specimens. The data in this report are
plotted against length rather than L/p in order to have
the test results in such a form as to facilitate conversion
to plot against L/p, the particular value of p, to be
used, to be determined by the method desired to present
the information for a particular purpose.
All specimens of this group consisted of three stiffeners
having a pitch of 4 inches. The stiffeners were
bent-up and built-up sections, using corrugated sheet
for the sides and back.
Part R
This group was designed to show the effect of the
following variables on the particular type of sections
shown in figure 3:
l. Depth of stiffeners with stiffener width remaining
constant.
2. Effect of thickness of stiffeners.
3. Effect of depth of corrugations.
As in part Q all specimens of this group consisted of
three stiffeners, having a pitch of 4 inches, with sides
and back bent-up and built-·up of corrugated sheet.
TEST APPARATUS
The test specimens were set up for test in the same
manner and in the same jig used for testing the stainless
steel specimens reported in Air Corps Information
Circular No. 697. Figures 24 and 25 show the jig used
and method of setting up the test specimens.
A 100,000-pound Olsen machine was used at Wright
Field and a 600,000-pound Olsen was used at the
Bureau of Standards on specimens exceeding the
capacity of the machine at Wright Field.
Areas were determined from the actual weight and
length of the individual specimens, using as the unit
weight of stainless steel 0.286 pound per cubic inch,
which was found to be an average value.
DISCUSSION
TYPES OF FAILURE
The types of failure of the specimens, listed in tables
II, III, and IV, were given the same classification as
those in Air Corps Information Circular No. 697 and
will be reviewed as follows:
Type A.- A failure due to the buckling of the outstanding
legs of the stiffener. It was usually confined
to the thinner stiffeners.
Type B.- When the combined thicknesses of the sheet
and stiffener were less than twice the stiffener thickness,
the failures ·were generally precipitated by buckling of
the stiffener welding flange.
Tyve C.- When the stiffener dimensions i.Jecame
s ufficient, the sides or backs of the stiffeners became
unstable, permitting the formation of waves in those
elements which led to their collapse.
Type D.-When a heavy sheet was used in the
presence of light stiffeners, the bowing of the heavy
sheet crushed the light stiffeners.
Tyve E.- When extreme differences between sheet
and stiffener thickness existed, failure often occurred
due to the pulling of slugs of welded material from the
lighter sheet by the heavier sheet.
Type F.- Due to the formation of severe buckles iu
the sheet, failure of stiffeners sometimes occurred due
to the distortion of the stiffener welding flanges by the
sheet buckling.
Tyve G.- This failure was due to column failure of
the specimens and was noticed before complete collapse.
Type H.- When there was a rough balance of the
elastic stability of all of the elements of the specimens,
the resulting failure was a general collapse of the complete
section.
Type /.- When the ratio of depth to width of the
stiffener exceeded about 1.5, the failure was due to
lateral instability of the stiffeners and was characterized
by a waving of the stiffener in a direction parallel to
the sheet.
Type J .-This classification includes all failures due
to poor welds and weld failures, due usually to the lack
of fusion of the welded material.
MA AND MC SERIES
This series of tests was conducted to show the effect
of reinforcing strips, as shown in figure 2, on the failing
stress of specimens. A direct comparison of stress with
and without these strips was made in figures 4 and 5;
the data for the failing stress without reinforcement
strips were taken from Air Corps Information Circular
No. 697, tables XII and XIV, and are included in
tables II and III of this report along with the data of
the lVIA and MC series. The specimens of the EA and
EC series of Air Corps Information Circular No. 697
are exactly the same as those having the same number
in the MA and MC series, respectively, except for the
addition of the reinforcing strips.
The tests indicate a general increase in failing stress
with the addition of the strips ·with but a few exceptions.
No definite conclusions should be drawn on the
effects of these strips on failing stress, however, since
it is felt that the tests reported in Air Corps Idormation
Circular No. 697 on these particular series were
influenced to some extent by weld failures, and since
the tests of this report were conducted on a small
number of specimens which were accompanied by the
usual scattering of test da~a .
It is of interest to note in figures 4 and 5 that for a
given depth the width of the stiffener within certain
limits has very little effect on the average failing stress
of the specimen. This is particularly notable in the
case of the stiffeners having a depth of 1 inch and 1Y2
inches, in which the width varies from ~ to 1 inch and
~ to 17~ inches, respectively. This point has been discussed
as a matter of interest in observing these data
only and must not be construed to mean that width has
110 effect on failing stress for all cases.
Q AND R SEUIES
(a) iVlethod of presenting data.
The results from the Q and R series tests shown in
tables IV, V, VI, and VII, have been presented in three
ilistinct groups of curves. The purpose of this grouping
is to present the data using three methods of calculating
failing stress as follows:
(1) Average failing stress.-Load taken by each specimen
divided by its total area.
(2) Stiffener stress (method A) .- The failing stress is
here calculated as a unit stiffener stress, being obtained
by dividing the total failing load of a given specimen
by the product of the number of stiffeners and the
effective stiffener area. The effective stiffener area
used by this method consists of the area of the stiffener
itself plus the area of the sheet whose width is equal to
the total stiffener width.
(3) Stiffener stress (method B) .- The stress in this
group is calculated as in (2) above, except that the
effective area of sheet here used is that of a sheet having
a width of 50 t, t being the sheet thickness.
These data are presented so that direct comparisons
can be made of the effect of these three methods of
calculating failing stress. The relative position of
the curves showing the effect of certain variations in
the component parts of the stiffeners do not change
with the method of computing failing stress. The
following discussion of tests of Q and R series will be
based on the average stress curves.
(b) Effect of reinforcing strips and backplate.
The following comments on effects of reinforcing
strips and backplate on failing stress are based upon
data shown in figures 6 and 7 of this report, these data
being for the Q series:
3
(1) It is apparent from a comparison of figures 6 and
7 that the effect of reinforcing strips varies with the
width of the particular stiffener under consideration.
(2) On the specimens with stiffener width of one
half inch (fig. 6) the reinforcing strip lowers the failing
stress, whereas figure 7 with stiffener width of 1 7~
inches indicates an increase in failing stress with the
addition of the reinforcing strips.
(3) The addition of the backplate is beneficial in all
cases as would be expected from consideration of additional
stabilizing of the stiffener section as a whole.
(4) The comparison between the built-up section to
the bent-up section, both sections with backplate,
shows that the bent-up section is but slightly superior
to the built-up section in the intermediate lengths when
the width of stiffener is one half inch. The stresses
obtained on the built-up and bent-up sections without
backplate differ by so small an amount as to be within
the experimental error, the amount of variation depending
to a considerable extent upon the method used
in calculating the failing stress.
(c) Effect of stiffener depth.
The data are obtained from the tests of the specimens
of the R series. Figure 8 shows a lowering of
failing stress for the shorter length of specimens with
an increase of depth from 1% to 1% inches. The deeper
stiffeners show a considerable increase in stress over
the shallower stiffeners in the greater lengths as is to be
expected, due to the lower value of L fp of t est specimens
for a given length. A plot of these data against
Lfp would show the depth of 1% inches even more
desirable as the data would then show a greater failing
stress in the whole short column range of L fp.
(d) Effect of stiffener thickness.
From tests of specimens of the R series, figure 9 shows
a general trend of lowering of failing stress with decreasing
stiffener thickness, but the data here shown
are insufficient to draw any conclusions as to the
amount of this lowering of stress. The tests of the
.020 inch stiffeners are more or less erratic for certain
specimens.
(e) Effect. of corrugation depth.
Tests on specimens of the Q and R series show that
iucreasing corrugation depth on these types of stiffeners
has a considerable effect on failing stress. It is
seen from figures 10 and 11 that increasing the corrugation
depth increases the failing stress, except on the
F type stiffener, which failed at the same stress with
either the one-fourth or five-sixteenth inch depth corrugations.
The failing stress on the C type stiffener
increases very appreciably with an increase of corrugation
depth from one-fourth to five-sixteenth inch .
CONCLUSIONS AND RECOMMENDATIONS
The addition of reinforcing strips at the welding
flanges of stiffeners can be used on particular stiffeners
to obtain higher failing stresses than those without
reinforcing strips. These strips may be used to advantage
on sheet-stringer combination whose stiffeners
fail as long columns and on particular types of stiffeners
within the short column range.
For stiffeners made up of corrugated sheet the backplate
or closing strip of the stiffener on the sheet side
4
is a dependable means of obtaining an increase in
failing stress.
Increasing the depth of stiffener from 1% to l Ys inch
allows failure of stiffener at a lower stress due to the
instability of the sides of the corrugated type of stiffener.
Tests indicate permissibility of using deeper sections for
longer columns to obtain maximum stress for this type
stiffener without lateral instability of section as a whole.
On stiffeners 1 inch wide and 1% inches deep a decrease
in stiffener thickness from 0.030 to 0.020 inch is
accompanied by decreasing failing stress in the shorter
lengths, but 0.020 inch thickness may be used to advantage
on the longer columns.
The quality of the spot-welding of these specimens
was very satisfactory . There were only a few cases of
poor spot-welds in these specimens and those occurred
where three thicknesses of material were welded together.
The quality of the spot-welding of these specimens
indicates that with experience and care in fabrication
spot-welding is a very satisfactory method of construction
to develop the full strength of stainless steel
sections.
REFERENCES
An increase in corrugation depth of the component
parts of these stiffeners is accompanied by an increase
in failing stress in depth up to five-sixteenths inch,
which was the maximum depth used in these tests.
I ncreasing corrugation depth appears to be the most
satisfactory method of obtaining high failing stresses in
the short length of stiffeners.
1. An investigation of the compressive strength
properties of stainless steel sheet-stringer combinations
by C. G. Brown and E. H. Sclrn·artz- Air Corps
Information Circular No. 697.
TABLE !.- Physical· properties of lest specimen material
(Material branch tests-reference series R35-247)
Observation of tho test data shows that the difference
in failing stress of comparable built-up and bent-up
sections is but small. It is believed that the built-up
section is more desirable for use at the present time
because of difficulties encountered in forming the bentup
sections with the present methods of construction.
Since the tests show that the most satisfactory
method of obtaining high failing stresses is by increasing
the corrugation depth of the stiffeners, it is recommended
that tests be conducted on sheet-stringer
combinations with corrugation depth of stiffeners
greater than five-sixteenths inch to obtain optimum
depth of corrugations.
Rpecimen Thick-no.
ness
-----
82-A-L __ o. 0110
82-A- 2 ___ .0110
82-A-3 ___ . 0108
86- A-L __ .0153
86-A- 2 ___ . 01:;0
86-A-3 ___ .0152
83- C-L_ .0207
83- C-2 _ _ .0207
83-C- 3 ___ . 0207
89- A-L __ .0294
89-A- 2 __ _ . 0296
89-A-3 ___ . 0297
1 No test.
Proportional limit
Tan- 0.0001
U . T . S. gent inch per inch set
------ - - -
(1) (1 ) (1)
185, 450 54, 600 80, 000
188,880 106. 500 129, 600
175, 820 65, 400 108, 500
176, 670 80, 000 100, 000
176, 970 85, 600 118, 500
185, 990 67, 600 86, 900
184, 540 77, 300 100, 500
184, 670 96, 500 118, 800
194, 160 101, 800 118, 800
195, 610 101, 300 188, 300
196, 910 100, 700 109, 500
Yield Elong-point
ation
(0.002 (per-inch
cent
p er inch) in 2 inches)
------
(1) (1 )
164, 540 3. 5
175, 000 3. 0
158, 820 8. 5
158, 670 7. 0
160, 530 6. 5
168.120 6. 0
167, 200 6.0
168, 800 6.0
174, 470 4. 5
175, 670 5. 0
174, 730 4. 0
Modu-
!us of
elas-ticity
(1,000
ponnd
p er
square
inch)
(1)
25, 25 0
0
0
0
0
0
0
0
00
24,08
26, 55
24, 68
26, 06
25, 70
24, 25
24, 05
23, 2
23, 37 0
25, 5 20
TABLE IL-MA and MC series (and corresponding EA and EC series) stiffener pitch= 2.50 inches-Test data and
calculations
Thickness Stiliener
Num- 'l'olal Total
Weight Average Failing Length Width bcr of area area sti f- 'l'y peof
Specimen no. (pounds) area load (inches) (inches) s tif- sheet feners Width D epth failure
(sqnare (pounds) Stiffener Sheet fen er (square (square cw- (D -
inch) (incb) (inch) inch) inch) inches) inches)
---------- --- --------- - - - --------------
MA304 _______ 0. 595 0. 443 53, 260 o. 030 o. 0105 4. 70 6. 06 3 0. 064 o. 379 0. 50 o. 50 F
MA305 __ ___ __ L 187 .442 48, 610 . 030 . 0105 9. 38 6. 05 3 . 064 . 378 . 50 . 50 G
MA306 ___ ____ l. 772 .439 37, 230 . 030 . 0105 14.11 6. 06 3 . 064 . 375 . 50 . 50 G
MA306Y.f _____ 2.365 .440 26, 860 . 030 . 011 18. 80 6. 06 3 . 067 . 373 . 50 . 50 G
MA306Y, _____ 2. 930 . 437 23, 090 . 030 . 0105 23. 46 6. 08 3 . 064 . 373 .50 . 50 G
MA306~- ---- 3. 536 . 439 17, 450 . 030 . 0105 28.15 6. 06 3 . 064 . 375 . 50 . 50 G
MA310a _____ L452 . 538 60, 930 . 030 . 0105 9. 44 6. 06 3 .064 . 474 .50 1. 00 J
MA310b _____ L452 . 538 57, 800 . 030 . Oll 9. 45 6. 01 3 . 066 .472 . 50 L.00 H
MA31L _____ 2. 861 . 536 56, 100 . 030 . 011 18. 64 6. 03 3 . 066 .470 . 50 l. 00 G
MA312 ______ 4. 203 . 538 47, 080 . 030 . 0105 27. 28 6. 03 3 . 063 . 475 . 50 1. 00 G
MA312)1 __ __ 5. 769 . 542 40, 870 . 030 . 0105 37. 24 6. 04 3 . 064 .478 . 50 LOO G
MA312Y, _ ___ 7. 079 . 538 30, 200 . 030 . 0105 46. 01 6. 06 3 .064 . 474 . 50 1.00 G
MA312~--- -- 8. 325 . 535 24, 450 . 030 . 011 54.50 6. 07 3 . 067 . 468 . 50 L 00 G
MA316. ____ __ 2.600 • 637 54, 175 . 030 . 010 14. 2ll 6. 08 3 . 061 . 576 . 50 l. 50 A
MA317 __ __ __ 5. 152 . 649 54, 300 . 030 . 0105 27. 77 6. 05 3 . 064 . 585 . 50 L 50 H
MA318 __ __ ___ 7. 438 • 629 51, 400 . 030 . 010 4L37 6. 05 3 . 061 . 568 . 50 L 50 G
MA325 ______ I. 769 • 655 69, 820 . 030 . 030 9. 43 6. 05 3 . 182 . 473 . 50 LOO H
MA326 _ ___ __ 3. 529 . 662 66, 530 . 030 . 0305 18. 65 6. 04 3 . 184 . 478 . 50 LOO G
MA327 ______ 5.159 . 661 59, 430 . 030 . 0305 27. 28 6. 06 3 .185 . 476 . 50 LOO G
MA33L _____ 3. 118 . 762 65, 440 . 030 . 030 14. 30 6. 06 3 . 182 . 580 . 50 L50 c
MA332 ________ 6. 047 . 763 65, 780 . 030 . 0305 27. 73 6. 05 3 .185 . 578 . 50 I. 50 H
MA333 __ _____ 9. 015 . 762 65, 600 . 030 . 0305 4L38 6. 07 3 . 185 . 577 . 500 L 50 A
MC540 ______ L578 . 589 64, 640 . 030 . 010 9. 35 6. 56 3 . 066 .523 l. 00 L 00 H
MC54L __ __ _ 3. 161 . 596 62, 285 . 030 . 011 18. 56 6. 56 3 .072 .524 L 00 LOO G
MC542 _ _____ 4. 666 . 589 52, 910 . 030 . 0105 27. 72 6. 55 3 . 069 . 520 LOO LOO G
MC546 _ ____ _ 2. 968 . 747 60, 750 . 030 . 0105 13. 91 7. 05 3 .074 . 673 L50 I. 50 c
MC547 __ ____ 5. 718 . 731 57, 960 . 030 . 011 27. 38 7. 05 3 . 078 . 653 J. 50 L50 c
MC548 ______ 8. 545 . 73Y 59, 200 . 030 . 011 40. 49 7.04 3 . 078 . 661 L50 1.50 G
MC552 _______ L938 . 72.) 74, 910 .030 .031 9. 35 6. 49 3 . 201 . 524 LOO 1.00 F
MC553 _______ 3.816 . 721 72, 970 . 030 .0305 18. 52 6. 56 3 . 201 . 520 LOO LOO G
MC554 ___ --- 5. 685 . 717 62, 310 .030 .030 27. 69 6. 56 3 . 201 . 516 LOO LOO G
MC.558. ______ 3.477 . 8765 75, 200 .030 .0305 13.88 7. 04 3 . 215 .6615 L50 1. 50 G
MC559 _______ 6. 809 .870 76, 300 . 030 .031 27. 37 7. 04 3 . 218 . 652 L50 L50 c
MC56Q _______ 10. 071 .870 73, 600 .030 .031 40.44 7. 04 3 . 218 . 652 L 50 L50 G
J!;A304a ___ ___ . 533 . 4025 49, 460 .030 .009 4. 63 8. 40 4 . 0756 .3269 .50 . 50 G
5
TABLE II. - MA and MC series (and corresponding EA and EC series) stiffener pitch=2.50 inches - Test data and
calculations - Continued
Thickness Stiffener
Average Num- Total T otal
Weight area Failing Length Width her of area area stif- Specimen no. Typeo (pounds) (square (polouandd s) Stiffener Sheet (inches) (inches) stif- (ssqhueaert e (fseqnuearrse Width D ep th failure inch) (inch) (inch) fener inch) inch) (W- (D-inches)
inches)
- ------ --- --- ------- ----------- -----
EA304h ____ __ o. 525 o. 3990 46, 190 0. 030 0.009 4. 60 8. 41 4 0. 0757 o. 3233 o. 50 0. 50 G
EA305a ______ 1. 044 . 3930 41, 600 .030 . 009 9. 30 8. 39 4 . 0755 . 3175 . 50 • 50 F
EA305h ____ __ 1. 070 . 4030 41, 400 .030 . 009 9. 29 8. 36 4 . 0752 . 3278 . 50 . 50 F
EA306a _____ _ 1. 598 . 4020 33, 775 .030 .009 13.88 8. 33 4 . 0749 . 3271 . 50 . 50 G
EA306h ___ ___ 1. 613 . 4045 ---------- .030 .009 13. 94 8. 36 4 .0752 . 3293 . 50 . 50 ---- --- EA310a ______ 1. 378 . 5265 60, 750 .030 .010 9. 15 8. 40 4 . 0840 .4425 . 50 1. 00 I
EA310b ______ 1. 372 . 5240 59, 720 . 030 . 010 9.15 8.38 4 .0838 .4402 .50 LOO I
EA31la ___ ___ 2. 759 . 5260 46, 450 .030 .009 18.34 8.38 4 . 0754 .4506 . 50 1.00 I
EA31lb ______ 2. 741 .5220 43, 250 .030 . 009 18. 33 8.38 4 . 0754 • 4466 .50 1. 00 G
E A312a __ ____ 4.083 .5325 42, 630 .030 .010 26. 79 8.43 4 . 0843 .4482 . 50 1.00 G
EA312h __ ____ 4.107 . 5355 45, 580 .030 . 009 26. 79 8.37 4 .0753 . 4502 . 50 LOO G
EA316a--- - - - 2. 518 .6575 51, 620 . 031 . 010 13. 39 8.49 4 . 0849 . 5726 . 50 1. 50 J
EA316b ___ ___ 2. 514 • 6550 55, 300 .030 . 009 13. 39 8.40 4 . 0756 .5794 . 50 1. 50 J
E A317a _____ _ 5. 015 .6550 52, 460 .03l .009 26. 82 8.42 4 . 0757 .5793 . 50 1. 50 I
EA317b_ ----- 5.035 . 6560 50, 250 . 031 -009 26. 82 8. 49 4 . 0764 . 5796 . 50 L50 I
EA318a ____ __ 7. 601 . 6605 44, 270 .031 . 009 40. 20 8. 40 4 . 0756 . 5849 . 50 1. 50 G
EA318b ______ 7. 594 . 6fi95 40, 410 . 031 . 009 40.24 8.47 4 .0762 . 5833 . 50 1. 50 G
EA325a ___ __ _ 1. 794 . 6855 67, 000 .030 .029 9.14 8. 43 4 . 2442 . 4413 . 50 1. 00 J
EA325b __ ____ 1. 776 . 6850 73, 850 . 030 . 029 9. 06 8.42 4 . 2440 . 4410 . 50 1. 00 I
EA326a ______ 3. 578 . 6840 70, 750 .030 . 029 18. 31 8. 41 4 . 2440 . 4400 . 50 1.00 I
EA326b ____ __ 3. 562 . 6800 45, 000 . 030 . 029 18. 32 8.44 4 . 2447 . 4353 . 50 1. 00 J
E A327a _____ _ 5. 247 . 6840 60, 510 .030 .028 26.82 8.41 4 . 2355 . 4485 . 50 1.00 I
EA327b ____ __ 5. 232 . 6825 55, 040 . 030 . 028 26. 78 8.41 4 . 2355 . 4470 . 50 1. 00 I
EA331a __ ____ 3. 102 . 8150 70, 410 . 030 .029 13. 31 8.42 4 . 2442 . 5708 . 50 L50 I
EA331b ____ __ 3. 121 . 8150 70, 750 . 030 .029 13. 38 8. 42 4 . 2442 . 5708 . 50 L 50 I
EA332a ______ 6.251 . 8155 69, 910 .030 .028 26. 78 8.50 4 . 2380 . 5775 .50 L50 J
EA332b __ __ __ 6. 321 . 8255 66, 630 .030 . 029 26. 79 8.39 4 . 2435 . 5820 . 50 L 50 I
EA333a ___ ___ 9.417 . 8180 62, 970 . 030 .029 40.20 8.45 4 . 2450 . 5730 . 50 L 50 G
EA333b_ --- -- 9.430 . 8190 66,000 . 031 .029 40. 25 8.45 4 . 2450 . 5740 . 50 L50 G
EC540a ______ 1. 555 . 5935 69, 330 .030 .010 9. 15 8.85 4 . 0886 .. 5049 LOO LOO G
EC540b ______ 1. 556 . 5936 71, 800 .030 .010 9. 15 8. 85 4 .0885 .5051 l.00 LOO G
EC54la ___ ___ 3.089 . 5900 48,450 .030 . 010 18. 29 8. 86 4 . 0886 . 5014 LOO LOO G
EC54lh ___ ___ 3.106 . 5930 63, 360 • 030 . 010 18. 31 8. 92 4 . 0892 . 5038 LOO 1. 00 G
EC542a ______ 4. 658 • 5920 48, 010 . 030 . 009 27. 48 8. 92 4 . 0802 .5118 LOO 1.00 G
EC542b ______ 4.638 . 5895 41, 210 .029 .009 27. 50 8.84 4 .0795 .5110 LOO L 00 G
EC546a ______ 3. 041 . 7880 48,000 . 031 . 009 13. 48 9.43 4 . 0849 . 7031 1. 50 L 50 J
EC546b ___ ___ 3.044 . 7890 62, 315 .031 . 009 13. 50 9. 46 4 . 0851 . 7039 L 50 1. 50 G
EC547a ______ 6.102 . 7900 63, 475 . 031 . 009 27.00 9.44 4 . 0850 . 7050 1. 50 L 50 H
EC547b ___ ___ 6.096 . 7885 60, 300 . 031 . 009 27. 03 9. 35 4 .0841 . 7044 1. 50 L 50 J
EC548a __ ____ 8. 990 . 7765 56, 270 .029 .009 40.49 9.45 4 . 0850 . 69 15 l. 50 L 50 G
EC548b_ - -- - - 9. 151 . 7880 56, 575 . 031 .009 40. 55 9. 44 4 . 0850 . 7030 1. 50 L50 J
EC552a ______ 2. 005 . 7630 83, 950 . 030 . 029 9.10 8. 99 4 . 2610 . 5020 L 00 1.00 H
EC552b _____ _ 2. 006 . 7625 80, 770 .030 .029 9. 20 8. 90 4 . 2580 . 5045 1.00 l. 00 J
EC553a ___ ___ 4.025 . 7690 75, 750 . 030 .029 18. 31 8. 93 4 . 2590 .5!00 1.00 1. 00 H
EC553b ______ 4.002 . 7625 74, 270 . 030 .029 18. 34 8. 91 4 . 2580 . 5045 I. 00 LOO G
EC554a ___ ___ 6. 026 . 7650 61, 280 .030 . 029 27.48 8. 94 4 . 2590 . 5060 1.00 LOO G
EC554b _____ _ 6. 035 . 7660 60, 770 .030 . 029 Zl.50 8.95 4 . 2595 . 5065 1. 00 LOO J
EC55Sa ______ 3. 804 . 9850 80, 280 . 031 .029 13. 50 9.42 4 . 2733 . 7117 1. 50 L 50 c
EC558b ____ __ 3. 812 . 9865 81, 750 .030 .030 13.48 9.50 4 . 2850 . 7015 L 50 1. 50 c
EC559a ___ -- - 7.610 . 9850 80, 130 . 030 .030 27. 02 9.50 4 . 2850 . 7000 1. 50 1. 50 H
EC559b __ ____ 7. 562 . 9785 ---- ------ . 031 . 029 27. 00 9. 43 4 . 2735 . 7050 \. 50 l. 50 --- ---- EC560a _____ _ ll. 321 . 9780 50, 000 .030 . 020 ''°· 47
9.37 4 . 2720 . 7060 l. 50 l. 50 J
EC560b ______ lL 431 . 9880 74, 600 . 030 . 030 40. 4-8 9. 50 4 . 2850 . 7030 l. 50 1.50 H
---- - -
T ABLE III. - MA and MC series (and corresponding EA and EC series) stiffener pitch=2.50 inches- Test data and
calculations
Metbod A Method B
Average
Failing Average fsatirleinssg Widtb of Stiffener Width of Stiffener
Specimen number load area (pounds sheet Area of Total failing sheet Area or Total fail ing
(pounds) (square sheet area stress sheet area stress inch) per acting at acting acting (pounds actin~ at acting acting (pounds
square stiffener (square (square per stiffener (square (square per inch) stress stress
(inches) inch) inch) square (inches) inch) inc!1J square
incb) inch)
- --- - - - ---- - - --- - - -- ------
MA304_ __ ____ ___________ 53, 260 o. 443 120, 300 2% 0. 028 0. 407 130, 700 I. 391 0. 0146 0. 394 135, 200
MA305 ____ ___ ___ ______ __ 48, 610 . 442 110, 000 2% .028 .406 119, 700 I. 391 . 0146 . 393 123, 600
MA306 ___ _______ ________ 37, 230 . 439 84,800 2% .028 . 403 92, 300 I. 391 . 0146 . 390 98, 000
MA306~-- -------------- 26, 860 . 440 61, 000 2% .029 . 402 66, 800 I. 453 . 0160 . 389 69, 000
MA306.J,2 __ _ --- ----- -- - -- 23, 090 . 437 52, 800 2% . 028 . 401 57, 600 I. 391 . 0146 . 388 59, 500
MA306K.-- - - - -- ----- - -- 17, 450 . 439 39, 700 2% . 028 . 403 43, 300 I. 391 . 0146 . 390 44, 700
MA310a __ ___ ________ __ __ 60, 930 . 538 113, 400 2% .028 . 502 121, 300 I. 391 . 0146 . 489 124, 600
MA310b __ __ ___ -- - ·------ 57, 800 . 538 107, 400 2% .029 . 501 115, ~00 1. 453 . 0160 . 488 118, 500
MA31L ___ _____ ____ _____ 56, 100 . 536 101, 500 2% . 029 . 499 112, 300 1. 453 . 0160 . 486 115,400
MA3:2 __________________ 47, 080 . 538 87, 500 2% . 028 . 503 93, 500 1. 391 . 0146 . 490 96, 100
MA312~ _ - --------- - ---- 40, 870 . 542 75, 300 2% . 028 . 506 80, 700 1. 391 . 0146 . 493 83,000
~±m~:::::·::::::::::: 30, 200 . 538 56, 100 2% .028 . 502 60, 100 I. 391 . 0146 . 489 61, 700
24, 450 . 535 45, 700 2% . 029 . 497 49, 100 1. 453 . 0160 . 484 50, 400
MA316 ____ ___ ___________ 54, 175 . 637 85,000 2% .026 . 602 89, 900 1. 328 . 0133 . 589 92, 100
MA317 ___ _____ _____ ___ __ 54, 300 . 649 83, 700 2% .028 . 613 88, 600 1. 391 . 0146 . 600 90, 600
MA 318 __________________ 51,400 .629 81, 700 2% .026 . 594 86, 500 1. 328 . 0133 . 581 88,400 MA325 ____ ___ __ ___ __ __ __ 69, 820 . 655 106, 400 2% . 079 . 552 126, 300 3. 828 . 1150 . 588 118, 700
9318-37- - 2
6
TABLE lII.-1\fA and MC series (and corresponding EA and EC series) stiffener pilch=2.50 inches-Test data
and calculations-Continued
Method A Mftbod B
Average
Average failing
Failing stress Width of Stiffener Width of Stiffener Specimen number load area (square (pounds sheet Area of Total failing sheet Area of Total failing (pounds) sheet area stress sheet area stress inch) sqpuearr e acting at acting acting (pounds acti ng at acting acting (pounds stiffener (square (square per stiffener (square (square per inch) s tress inch) inch ) square stress inch) inch) square (inches)
inch) (inches)
inch)
---- ---- - --- - --- - --- ---- ----
MA326. ------- -- -- - - ____ 66, 530 o. 662 100, 400 2% 0. 080 o. 558 119, 300 3.888 0. 1187 0. 597 111, ;;oo MMAA333217 ___ - -__-_--_-__-_-_--_-__-_--_-__--_ 59, 430 . 661 89, 800 2% .080 • 556 107, 000 3. 888 .1187 . 595 99, 900 65, 440 . 762 85, 800 2% . 079 . 659 99, 300 3. 828 .1150 . 695 94, 200 MA332. ____ - - -- - - -- - ____ 65, 780 . 763 86, 250 2% .080 . 658 100, 000 3. 888 . 1187 . 697 94, 300 MA333 ___ ___ ________ __ __ 65, 600 . 762 86,000 2% . 080 . 657 99, 800 3. 888 . 1187 . 696 94, 200 MC540 ___ __ ____ __ _______ 64, 640 . 589 109, 700 Hfl . 041 . 564 114, 600 1. 328 . 0133 . 536 120, 600 MC54l __ ____ ___ ________ _ 62, 285 . 596 104, 600 4J.f; . 045 . 569 109, 400 I. 453 . 01 60 . 540 115, 300 l'vIC542. ____ __ -- - ---- - --- 52, 910 . 589 89, 900 4J.1i . 043 . 563 94, 000 I. 391 . 0146 . 535 98, 800 MC546 _________ _________ 60, 750 • 747 81, 300 5% . 059 . 732 82, 900 I. 391 . 0146 . 688 88, 300 M C547 _ --- --- --- ---- - -- - 57, 960 . 731 79, 200 5% . 062 . 715 81, 100 1.4 53 . 0160 . 669 86, 600 MC5~8. ______ ___ ____ ___ _ 59, 200 . 739 80, 100 5% .062 . 723 81, 900 1.463 . 0160 . 677 87, 400 M C552 _____________ _____ 74, 910 . 725 103, 300 4Ys .128 . 652 114, 900 3, 953 .1227 . 647 115, 700 M C553 ____ ____ -- ----- --- 7_2,\970 . 721 101, 200 4Ys . 126 . 646 113, 000 3. 888 . ll87 . 639 114; 200 MC554. ____ ___ . - -- - -- __ . 62, 310 . 717 86, 900 4Y, . 124 . 640 97, 300 3. 828 .1150 . 631 98, 700 MMCC555589 ._ -__- -_-__- -_-_-_-_-__-_-_- -_-_-_-_ 75, 200 . 8765 85, 900 5% .172 . 8335 90, 300 3. 888 . 1187 . 780 96, 400 MC560 ___ ___ __ ___ ______ _ 76, 300 . 870 87,600 5% .174 . 826 92, 300 3. 953 . 1227 . 775 98, 400 73, 600 . 870 84, 500 5% . 174 . 826 89, 100 3. 953 . 1227 . 775 94, 900 EA304a ______ ___ -- -- - --- - 49, 460 . 4025 122, 800 372 . 0315 . 3584 138, 000 I. 203 . 0108 . 338 146, 300 EA304b . - - --- - ------ ---- 46, mo . 3990 115, 900 3Yi . 0315 . 3548 130, 300 1. 203 . 0108 . 334 138, 300 EA305a .. . ... ____ --- - -- - - 41, 600 . 3930 105, 900 a;2 . 0315 . 3490 119, 300 1. 203 . 0108 . 328 126, 800 EEAA330065ab _ ._._ -__-_--__- -__-_-_-_-_- -- ------ 41, 400 . 4030 102, 800 3j~ . 0315 . 3593 115, 300 l. 203 . 0108 . 339 122, lOO 33, 775 .4020 83, 900 37',z . 0315 . 3586 94, 200 1. 203 . 0108 . 338 99,800 EA306b __ -- - -- ------- - -- - - -- - --- -- . 4045 ------- --- --- - ------- - - ----- -- -- ---------- -- -------- -- -- ------ -- --- -~ 0133 · -- -- - ~ 456" EA31Qa __ ___ __ _______ ___ 60, 750 . 5265 115, 300 372 . 0350 . 4775 127, 200 1. 328 -- -------- EA3l0b. - -- - -- ------- - - - 59, 720 . 5240 114, 000 133, 300 EA3lla ___ __ __ __ ___ _____ 372 . 0350 . 4752 125, 700 1. 328 . 0133 . 454 131,600 46, 450 . 5260 88, 250 372 . 0315 . 4821 96, 300 1. 203 . 0108 . 46l 100, 700 EEAA331112 ba ____ -_-_-__-_-_- -. -__-_- -. -_-__--_ 43, 250 . 5220 82, 900 372 . 0315 . 4781 90, 500 1. 203 . 0108 . 4.17 94, 500 42, 630 . 5325 80,000 :~ ! '2 . 0350 . 4832 88, 300 1. 328 . 0133 . 462 92, 200 l~A312b ____ - ----- -- - - 45. 580 . 53fi5 85, 100 :~! 2 . 031 5 . 4817 94, 500 l.20:J . 0108 .461 98, 800 EA316a __ _____ . ____ .. __ _ 51, 620 . 6575 78, 500 3Y.i . 0350 . 6076 84, 900 J. 328 . 0133 . 586 88, 200 l<:A316b __ __ ---------- - - 55, 300 . 6550 84, 400 372 . 031 .) . 6109 90, 400 1. 203 . 0108 . 590 93, 700 EA317a __ _____ __ ___ -- ---- 52, 460 . 6550 80, 100 372 . 031 5 . 6108 85, 800 1. 203 . 0108 . 590 8 ,900 EA317b __ -- --- -- -- ------ 50, 250 . 6560 76, 500 3Yz . 0315 . 6111 82, 200 I. 203 . 0108 . 590 85, 200 EA318a. ... __ _______ _____ 44, 270 . 6605 67, 000 372 . 0315 . 6164 71, 700 1. 203 . 0108 . 596 74, 300 EA318b __ ------- -- - - - -- - 40,410 . 6595 61, 200 372 . 031 5 . 6148 65, 700 1. 203 . 0108 . 594 68, 000 EA325a __ ________ _- - --- _ 67, 000 . 6855 97, 800 3}~ . 1015 . 5428 123, 400 3. 705 .1075 . 549 122, 000 EA325b _____ ---- -- -- - - -- 73, 850 . 6850 107, 800 3}.-2 .1015 . 5425 136, 200 3. 705 .1075 . 5-19 134, 500 EA326a _________ ____ - - - - - 70, 750 . 6840 103, 700 3H .1015 . 5415 130, 500 3. 705 .1075 . 548 129, 200 EEAA332276ab _ ._._ -_-_-_-_-_-_-__-_-_-_-_-_--_-_ 45, 000 . 6800 66, 200 3}'1 . 101 5 . 5368 83,800 3. 705 . 107.5 . 543 82, 900 60, 510 . 6840 88, 500 3)1 . 0980 . 5465 110, 700 3. 578 . 1003 . 549 110, 300 EEAA33237lab _ ____ -__-_--_-__-_--_-__-_--__-_--_ 55, 040 . 6825 80, 750 3)1 . 0~80 . 5450 101, 000 3. 578 . 1003 . 547 100, 600 70, 410 . 8150 86, 500 3)1 . 1015 . 6723 104, 700 3. 705 . 1075 . 678 103, 800 E A33lb. ____ - --- --- -- - - - 70, 750 . 8150 86, 900 372 . .1015 . 6723 105, 300 3. 705 .1075 . 678 104,400 EA332a ____ __ __ . _- - ----- - 69, 910 . 8155 85, 700 3)1 . 0980 . 6755 103, 400 3. 578 .1003 . 678 103, 200 EA332b __ -- - -- -- --- - ---- 66, 630 . 8255 80, 700 3Yz . 1015 . 6235 97, 500 3. 705 .1075 . 689 96, 800 EA333a .. . __ _- -- - - - - - ____ 62, 970 . 8180 77, 000 3)1 . 1015 . 6745 93, 300 3. 705 .1075 .681 92,400 EECA5343D3ab _._ -_-_-__-_-_-_- ----- ____ 66, 000 . 8190 80, 600 3Yz . 1015 . 6755 97, 700 3. 705 . 1075 . ~81 96, 900 E C540b __ ------ -- 69, 330 . 5935 117, 000 fl}-2 .055 . 5599 123, 800 1. 328 . 0133 . 518 133, 800 E C54Ja ____ ------ ___-__--_- - 71, 800 . 5936 121,000 [1 ~1 . 055 . 5601 128, 200 l. :128 . 0133 . 518 138, 600 48, 450 . !\900 82, 100 .e.J 2 . 055 . 5564 87, 000 1.328 . 0133 . 515 94, 200 E C54l b ___ ---------- - - 63, 360 . 5930 106, 900 !ih . 055 . 5588 113, 400 1. 328 . 0133 . 517 122, 500 EC542a ______ - - ----. - -- .. 48, 010 . 5920 81, lOO 5Yz . 0495 . 5613 85, 500 1. 203 . 0108 . 523 91, 900 EC542b ____ _____ ___ 41, 210 . 5895 87, 000 572 .0495 . 5605 73, 500 1.203 . 0108 .522 78, 900 EC54fo ______ ___________
EC546b ____ _____ _____ ____ 48, 000 . 7880 60, 900 7Yz . 0675 . 7706 63, 300 l. 203 . 0108 . 714 67, 200 EC547a __ ____ . ___ __ ____ __ 62, 315 . 7890 79, 000 7Yz . 0675 . 7714 80, 700 1. 203 . 0108 . 715 87, 100 63, 475 . 7900 so, 300 7Yz .0675 . 7725 82, 100 1. 203 .0108 . 716 88, 700 EC547b __ ____ __ - - - -- - ____ 60, 300 . 7885 76, 500 772 . 0675 . 7719 78,000 l. 203 .0108 . 715 84, 300 EE CC554488ab- _-__--__--_-__-_-_-_-_- -. -__- -_-_-_ 56, 270 . 7765 72, 500 772 . 0675 . 7590 74, 100 I. 203 .0108 . 702 80, 100 E C552a .. __ ____ ______ ____ 56, 575 . 7880 72,000 772 . 0675 . 7705 73, 300 l. 203 . 0108 . 714 79, 200 E C552b .. ____ __________ __ 83, 950 . 7630 110, 200 572 .1595 . 6615 126, 900 3. 705 .1075 . 610 137, 600 80, 770 . 7625 106, 000 572 '1595 . 6640 121, 600 3. 705 .1075 . 612 131, 800 EC553a. . _______ -- -- - - ___ 75, 750 . 7690 98, 500 5)1 . 1595 .6695 113, 300 3. 705 . 1075 . 618 122, 600 EC553b __ ______ __________ 74, 270 . 7625 97, 400 572 .1595 . 6640 111, 800 3. 705 .1075 . 612 121, 300 EECC555544ba. . •_ ____________ _-_-_-_--_-_-_-__- -_ 61, 280 . 7650 80, 100 5)1 .1595 • 6655 92, 100 3. 705 .1075 . 613 100, 000
60, 770 . 7660 79, 400 572 .1595 .6660 91, 200 3. 705 . 1075 . 614 99, 000 EC558a ___ ______ _ --- - -- - - 80, 280 . 9850 81, 500 772 . 2175 . 9292 86,400 3. 705 . 1075 . 819 98, 100 EC558b ____ ____ ___ _______ 81 , 750 . 9865 82, 900 772 '· 2250 . 9265 88, 300 3. 828 . 1150 . 817 100, 000 EC559a_ ___ __ __ _ .. __ . __ _. 80, 130 . 9850 81, 400 772 . 2250 . 9256 86, 700 3. 828 .1150 .815 98, 300 EC559b ______ ____ ____ ___
EC560a ___ _____- - --- - ---- --------- - . 9785 ----- ---- - ---- --- ---- - --- --- ---- ---- ---- -- -------- -- ------- -- --- --------- - ------ ---- -- ---- ---- 50, 000 . 9780 51, 100 772 . 2175 • 9235 54, 200 3. 705 . 1075 . 814 61, 400 EC56Qb ________ ___ . -- - -- - 74, 600 I .9880 i5, 500 7!-1 . 2250 .9280 so, 300 3. 828 . ll50 .818 91, 200
7
TABLE IV.- Q series-Stiffener pitch=4 inches-Number of stij)'eners, 3-Test data and calculations
Speci-men
num-her
Q
Q
70.3 ....
704 ....
8 705 ....
709 ....
710 ....
Q 711. ... I 715 ....
716 ....
717 ....
721. ...
722 ....
~ Q
Q
Q
Q
Q
Q
Q
Q
Q
723 ....
724 ....
725 . ...
726 ... .
727 ....
728 ____
729 ....
730 ....
781. ...
732 ....
733 ....
734. .. .
735 ____
739 ____
740 . ...
741. ...
Q75L. . .
Q 752 ....
Q753 ....
Q757 ____
Q758 ....
Q759 ....
Q763 ____
Q764. .. .
Q765 ....
Q769 ....
Q770 ___
Q77L. ..
Q775 ____
Q776 ... .
Q777 ....
Q78L. ..
Q782 ....
Q783 ....
Q787 ____
Q788 ____
Q789 ____
Q793 ....
Q794 ....
Q795 ____
Q796 ....
Q797 ____
Q798 ____
Q799 __ __
Q800 ....
Q80L. ..
QS02 ....
Q803 ....
Q804 .•. .
Q805._ __
Q806-. ..
Q807 ____
Q81L. ..
Q812 ....
Q813 ....
Q823 ....
Q824 ....
Q825 ____
Q829 ....
Q830 ....
Q83L. ..
Q835 ....
Q836 ....
Q837.. . .
Q84L. ..
Q842.. ..
Q843 ___
T ype
of
section
--
A
A
A
A
A
A
B
B
B
B
R
R c
c
c
c
c
c
c
c
c
u
c
c
D
D
D
E
E
E
Ji;
E
E
F
F
F
,F,
F
A
A
A
A
A
A
B
B
B
B
B
B c
c
c
c
c
c
c
c
c
c
c
c
D
D
D
E
E
E
E
E
E
F
F
F
F
F
F
Weigbt
(pounds)
----
1. 792
3. 589
5. 368
2.413
4. 780
7. 239
2.004
4. 026
6. 092
2. 65fi
5. 3-13
7. 964
2. 039
4.060
6. 082
2. 235
4.467
6. 705
2. 654
5. 398
7. 938
2. S:,9
5. 747
8. 534
2. 476
4. 950
7. 384
2. 749
5. 469
8. 219
3. 383
6. 774
JO. 071
3. 310
6. 657
9. 906
3. 968
7. 995
11. 975
2. 351
4. 696
7.046
3.065
6. 170
9. 203
2. 618
5. 263
7. 907
3. 355
6. 811
10.126
2. 880
5. 762
8. 602
3. 169
6. 332
9. 571
3. fiOO
7. 232
10. 677
3. 879
7. 820
11. 632
:,, 419
6. 851
10. 252
3. 300
6. 565
9. 825
4. 042
8. 062
12.190
4. 507
9.004
13. 437
5. 33.5
10. 6.52
15. 90
•
Tbickness
Average Failing area load (square (pounds) Stiffener Sheet inch) (inch) (inch)
- -----------
0. 5245 53, 740 0. 030 0. 0105
. 525 .52, 040 . 030 . 0105
. 524 4fi, 500 .O:JO . 010
. 706 67, 530 . 030 . 031
. 699 64, 850 . 030 . 0305
. 706 60, 210 . 030 . 031
. 567 55, 080 .o:;o . 0105
. 567 51, 440 . 030 . Oll
. 573 49, 960 . 030 . 011
. 748 71, 150 . 030 . 030
. 7525 m.560 . 030 . OR15
.749 57, 400 . 030 . 081
. 581 63, 240 . 030 . 011
. 580 57, 820 . 030 . 010
. 578 54, 020 . 030 . Oil
. 639 72, 450 .030 . 011
. 6375 72,420 . 030 . Oil
. 638 59, 800 . 030 . 0105
. 757 72, 680 . 030 . 0305
. 770 69, 510 . 030 . 0315
. 756 50, 940 . 030 . 030
. 809 82, 560 . 030 . 0305
. 820 82, 680 . 030 .031
. 812 64, 840 .030 . 030
. 682 76, 730 . OoO . 0105
. 6815 72, 870 . 030 . 0105
. 678 61, 220 .030 . 0105
. 735 78, 890 . 030 . 011
. 730 66, 700 . 030 . 011
. 731 64, 000 . 030 . 011
. 903 87, 190 . 030 . 0305
.904 83, 120 . 030 . 03LO
.895 76, 700 .oao . 030
. 841 98, 060 . 030 . 011
. 847 86, 990 .OoO . 011
. 840 75, 400 . 030 . 011
1. Oll 107, 400 ; 030 . 0305
l.015 96. 300 . 030 . 0305
l. 015 79, 450 . 030 . 031
. 647 63, 500 .030 . 011
. 647 63, 420 .030 . 0105
. 647 53, 750 .030 . 0105
. 843 82, 910 . 030 . 0305
. 849 79, 690 . 030 . 031
. 845 68, 650 . 030 . 031
. 690 74, 960 . 030 . 0105
. 694 69, 660 .OoO . 011
. 695 60, 100 . 030 . 011
.884 86, 580 . 030 . 0305
.808 83, 970 . 030 . 0315
. 891 69, 200 . 030 . 030
. 794 76, 480 . 030 . 0105
. 794 74, 350 . 030 . 0105
. 790 74, uo . 030 . 0105
. 871 97, 570 . 030 . Oll
. 870 88, 890 . 030 . 011
. 878 82, 620 . 030 . 011
. 993 93, 590 . 030 . 031
. 995 86, 850 . 030 . 031
. 980 76, 500 . 030 . 030
I. 074 120, 400 . 030 . 030
l. 076 109, 900 . 030 . 031
1.068 98, 700 . 030 . 030
. 916 109, 400 . 030 . 011
. 920 104, 200 . 030 . 0105
. 920 81, 500 . O;~O . 011
. 854 90, 120 .030 .011
. 851 85, 710 . 030 . Oll
.848 77, 400 .030 . 011
l. 046 102, 800 . 030 . 030
I. 043 99, 100 . 030 . 030
1. 052 80, 400 . 030 . 030
l. 088 128, 400 . 030 . 0105
I. 086 127. 900 .030 . OllO
1 080 88, 800 . 030 . 0110
1. 284 142, 300 . 030 . 031
1. 273 133, 300 . 030 . 031
l. 279 I 106, 900 . 030 . 031
Totfll Total Corrugation Stiffener
Lengtb Width area area (inches) (inches) Sheet stiffeners (square (square Pitch Depth Width Depth
(inch) (inch) (inch) (inch) (W- (D- inches) inches)
------------ ----------
ll. 94 0. 06 0. 095 0. 4295 }i :y,. 0. 500 1%
23. 02 9. 06 . 095 . 430 J.-:\ :Y,o .. 500 1%
35. 86 Y. 06 . 091 . 433 )".'\ 'ii• . 500 1%
11. 95 0. 06 . 281 . 425 ~ :y,. . 500 l ~~
2i.. 91 9. 06 . 276 . 4z:, ;2 ~,. . 500 1%
35. 87 9. 08 . 282 . 424 ;2 'Vis . 500 1%
12. 37 9. 04 . 095 . 472 )".'\ :Y,o . 500 1%
24. 81 9. 04 . 100 . 467 ~ 1-16 . 500 1%
37. 22 9. 05 . LOO . 473 h :Y,s . 500 1%
12.42 9. 06 . 272 . 476 ;2 :y,. . 500 1%
24. 82 9. 06 . 285 . 4675 ~ ., . . 500 13,8
37. 71 Y. Oti . 281 . 468 ;2 ~;. . 500 1 ~
12. 27 9. 07 . 100 . 481 ~~ % . 500 1%
24. 52 9. 07 . 091 . 489 )".'\ % . 500 1%
36. 76 9. 07 . 100 . 478 )".'\ % . 500 l}S
12. 25 9. 05 . 100 . • 509 )".'\ H• • 500 1%
24. 51 9. 03 .099 . 5o85 ~ ;" . 500 1%
36. 77 9. 03 . 095 .54:, ~ 'Vis . 500 1%
12. 27 9. 05 . 276 . 481 }~ % . 500 1%
24. 52 9. 05 . 285 .485 M ~ . 500 H
36. i3 9. 05 . 271 . 480 ~2 % . 500 118
12. 27 9. 06 . 276 . 533 i~ 'Vi 6 . 500 1%
24. fi t 9. 07 . 281 . ,539 J-2 :Y.• . 500 1%
36. 75 9. 06 . 272 . 540 H ~16 . 500 1J
12. 72 9. 05 . 095 . 537 ;2 :Y,o . 500 1%
25. 42 9. 04 . 095 . 5865 H ~16 . 500 1%
38. 11 9. 06 . 095 . 583 H :y,, . 500 J%
13. 10 0. 08 .100 . 635 H :Y,o . 500 1%
26. 22 0. 06 . 100 . 630 ~ :Y,o . 500 1%
39. 33 9. 07 .100 . 631 ~ H• . 500 1%
13. 12 9. 06 . 276 . 627 )".'\ Yi• . 500 1%
26. 21 9. 06 . 281 .623 16 'i4• . 500 1%
39. 30 9.06 272 . 623 )".'\ J1 s . 500 1%
13. 78 9. 06 . LOO . 741 Vi ~; . . 500 1%
27. 49 9. 07 . 100 . 747 H ~1 · . 500 1%
41. 25 9. 05 . 100 . 740 ;2 Hs . 500 1%
13. 73 9. 07 . 277 . 734 H J1o .500 1 ~8
27. 48 9. 07 . 277 . 738 H :y,. . 500 l ~··
41. 26 9. 06 . 281 . 734 H :Y,o . 500 1 ~8
12. 72 10. 09 .111 . 536 H :Y,o 1}2 1%
25. 43 10. 06 .106 . 541 H Ho 1).0 1%
38.10 10.06 .106 . 541 ~ J1o Hi 1%
12. 72 10.07 . 307 . 536 J-2 =}16 H-2 1%
25. 43 10. 08 . 312 . 537 )".'\ 'Vi• H2 1%
38. 08 10. 06 . 312 . 5>3 J-2 :y,. J}2 1%
13. 26 10. 05 . 106 . 584 H J1o l J.-:\ 1%
26. 49 10. 03 .110 . 5S4 ;o ~1. 1;2 1%
39. 77 10.04 .110 . 585 ~ Jio 1;2 1%
13. 28 10. 06 . 306 . 578 J-2 :y,. H'.i H8
26. 52 10. 06 . 3 17 . 581 H :y,. 1;2 1%
39. 74 10. 05 .i!02 . 5S9 H 'Vio 1;2 1%
12. 69 10. 05 . 106 . 688 H % H-2 HS
25. 39 10. 07 . 106 . 688 H % 1)6 IJ8
38. 07 10. 05 .106 . 684 }2 }8 1 ~ 1%
12. 72 10. 06 .111 . 760 ~ ~16 J ~ 1%
25. 42 10. 05 . 111 . 759 H Jic 1 H 1%
38. ll 10. 07 . lll . 767 )'.! ?1s H1' l J
12. 68 10. 04 . 312 . 681 H' l-s 1~ 1%
25. 41 10. 06 . 312 . 683 ).'2 ).8 lH 1%
38. 05 10. 06 . 302 . 678 ;2 }8 l~ 1.%
12. 63 10. 06 . :;02 . 772 H ~16 1;2 l '.)
25. 42 10. 06 . 012 . 764 )".'\ Ho H2 1%
38.10 10. 06 . 312 . 756 )".'\ :y,. 1'2 118
lo. 03 10. 05 .111 . 805 H• :Vie 1;2 1%
26. 02 10. 03 .105 . 815 )".'\ :y,, 1 H 1%
38. 99 10. 05 . 111 . R09 J-2 :y,. 1>2 1%
13. 52 10. 07 . J 11 . 743 H '.)fo 1;2 1%
26. 99 10. 07 . lll . 740 F• :Y,o 1;'2 1%
40. 50 10. 06 . 111 . 737 H :Y,o 1;2 1%
13. 5~ 10. 06 . 302 . 744 '"' :y,. 11.2 1%
27. 02 10. 04 . 301 . 742 ~~ :Y,o \}<\ J%
40. 49 10. 06 . 302 . 750 H ~16 1;2 1%
14. 50 10.06 . 106 . 982 H Yi• lH 1%
29. OJ 10. 08 . J 11 . 975 ~~ He 1)-2 1%.
43. 51 10. 03 . Ill . 969 ~:! Mts I ~ 1%
14. 52 10. 06 . 312 . 972 )-2 Ho 1),2 1%
29. 01 10. 06 . 312 . 961 )-2 'Vi• 1~ 1%
43. 49 JO. 05 . 312 . 967 )-2 ~1· IH 1%
Type
of
fail-ure
--
I
I
l
I
I
G c
I
I
I
I
G
I
I
G
I
I
G
I c
G
I
I
I
I
I
I
I
Q
I
II
(]
I
A
A
Q
A
A
0 c
G
G c
c
G c
G
G c
c
G c
c
c
c
c
G c
G
G
H
H
G
H
H
G c
c
Q
A
G
G c
G
G c
G
G
8
TABLE V.-Q series-Stiffener pitch = 4 inches-Number of stiffeners, 3-Test data and calculations
I Method A Method B
Average failing I -
Type Failing Average stress Width of Stiffener Width of Stiffener Specimen n9. of load area Area of Total failing Area of Total failing section (pounds) (square (pounds sheet act- sheet area stress sheet act- sheet area stress inch) sqpuearr e ing at acting acting (pounds ing at acting acting (pounds stiffener stiffener inch) str ess (square (square per
stress (square (square per
(inches) inch) inch) square (inches) inch) inch) square
inch) inch) - -------- --- - - - ---- -- Q703__ __ _____ ___ A 53, 740 0. 5245 l02,400 2% 0.028 0. 4575 117, 400 1. 391 o. 0146 0.444 121, 000 Q704 ______ __ __ __ A 52,040 . 525 99, 000 2% .028 .458 113, 500 1. 391 . 0146 . 445 117, 000 Q705 _____ _ -- - - - - A 46, 500 .524 88, 700 2% . 026 . 459 101, 300 ]. 328 . 0133 .446 104, 300 Q709 _____ _______ A 67, 530 • 706 95, 600 2% . 081 .fi06 133, 500 3. 953 .1227 .548 123, 300 Q710 _____ _____ __ Qm _____ __ _____ A 64, 850 .699 92, 800 2% . 080 . 503 128, 800 3. 888 .1187 .542 119, 500
Q715 _____ ____ ___ A 60, 210 . 706 85, 200 2% .081 . 505 119, 300 3. 953 . 1227 . 547 110,000 Q716 _____ __ ____ _ B 55, 080 . 567 97, 100 2% . 028 . 500 110, 200 1. 391 . 0146 .487 113, 200 Q717 __ ___ __ _____ B 51,440 . 567 90, 700 2% . 029 .496 103, 600 1.453 . 0160 .483 106, 400 Q72l__ ____ __ ___ _ B 49, 960 • 573 87, 200 2% .029 . 502 99,400 1. 453 . 0160 .489 102, 200 Q722 _____ ______ _ B 71, 150 . 748 95, 100 2% . 079 . 555 128, 300 3. 828 .1150 . 591 120, 400 Q723 _____ _____ __ B 67, 560 . 7525 89, 800 2% .083 . 5505 122, 700 4. 018 . 1267 . 594 113, 700 Q724 _____ ___ __ __ Bc 57, 400 . 749 76, 600 2% . 081 .549 104, 500 3. 953 .1227 .591 97, 100 Q725 ___ ___ ______ c 63, 240 . 581 108, 800 2% . 029 .510 124, 000 1.453 .0160 .497 127, 200 Q726 _____ _______ c 57, 820 . 580 99, 600 2% . 026 . 515 112, 300 I. 328 . 0133 . 502 ll5, 200 Q727 __ ___ ___ ___ _ c 54,020 .478 93, 500 2% .029 . 507 106, 500 1.453 . 0160 .494 109, 400 Q728 ______ _____ _ c 72, 450 . 639 113, 400 2% .029 .568 127, 700 1.453 . 0160 . 555 130, 600 Q729. ________ ___ c 72, 420 . 6375 113, 600 2% .029 . 5675 127, 500 1. 453 . 0160 . 555 130, 300 59, 800 .638 93, 700 2% .028 . 571 104, 600 L 391 . 0146 . 558 107, 200 Q730 _____ ___- -- - c 72, 680 . 757 96, 000 2% . 080 . 561 129, 600 3. 888 .1187 . 600 121,300 Q731__ ____ ______ c 69, 510 . 770 90, 300 2% .083 . 568 122, 300 4. 018 .1267 . 612 113, 500 Q732 ____ ________ c 59, 940 . 756 79, 300 2% . 079 . 564 106, 300 3. 828 .1150 . 600 100, 000 Q733 _____ __ _____ c 82,560 .809 102, 000 2% . 080 . 613 134, 700 3.888 .1187 . 652 126, 500 Q734 ____ ______ __ c 82, 680 . 820 100, 800 2% . 081 . 620 133, 400 3. 953 .1227 . 662 124, 800 Q735 ___________ _ c 64, 840 . 812 79, 800 2% . 079 . 619 104, 700 3. 828 . 1150 . 655 99, 000 Q739 ______ ______ Q740 ______ __ ___ _ D 76, 730 .682 112, 500 2% . 028 . 615 124, 800 I. 391 . 0146 .602 127,400
Q74L ____ ___ __ _ D 72, 870 . 6815 106, 800 2% . 028 . 6145 118, 400 1. 391 . 0146 . 601 121, 200 Q75L_ ___ _______ D 61, 220 .678 90, 300 2% . 028 .611 100, 200 1. 391 .0146 • 598 102, 400 Q752 ____ __ _____ _ E . 78, 890 . 735 107, 300 2% . 029 . 664 118, 800 1.453 .0160 • 651 J.21, 200 E 66, 700 . 730 91, 300 2% . 029 . 659 101, 300 I. 453 . 0160 . 646 103, 300 QQ775537 ____ _-_- -__-_-_- -_-__--_ E 64, 000 . 731 87, 500 2% .029 . 660 96, 900 1.453 . 0160 . 647 98, 800 Q758__ ____ _____ _ E 87, 190 . 903 96, 500 2% .080 . 707 123, 300 3. 888 .1187 . 746 116, 800 Q759 __ ________ __ E 83, 120 . 904 92,000 2% . 081 . 704 . 118, 200 3. 953 .1227 . 746 111, 400 Q763 ______ __ __ __ E 76, 700 .895 85, 700 2% . 079 . 702 109, 300 3. 828 .1150 . 738 104, 000 Q764 ________ ____ F 98, 060 .841 116, 700 2% . 029 . 770 127, 300 1. 453 . 0160 . 757 129, 500 Q765 ___ __ ____ ___ F 86, 990 .847 102, 600 2% .029 . 776 112, 100 1.453 . 0160 . 763 114, 000 Q769 __________ __ F 75, 400 . 840 89,800 2% . 029 • 769 98, 200 I. 453 . 0160 . 756 99, 700 Q77o ______ __ __ __ F 107, 400 1. 011 106, 300 2% .080 . 814 132, 000 3.888 .1187 .853 126, 000 Q77L_ ___ __ ____ _ F 96, 300 1. 015 94, 800 2% .080 . 818 117, 700 3.888 .1187 . 857 112, 300 l•' 79, 450 I. 015 78, 300 2% . 081 .815 97, 500 3. 953 .1227 . 857 92, 700 Q775 _____ ____ __ _ A 63, 500 . 647 98, 100 5% .062 . 598 106, 300 1.453 . 0160 .552 115, 000 Q776 ____ __ __ ___ _ A 63, 420 . 647 98, 000 5% . 059 . 600 105, 600 1. 391 . 0146 . 556 114, 000 Q777 ____ ______ __ A 53, 750 . 647 83, 000 5% .059 . 600 89, 600 1. 391 . 0146 .556 96, 700 Q78L ___ ___ ____ A 82, 910 . 843 98, 300 5% .172 . 708 117, 200 3.888 . 1187 .655 126, 600 Q782 _____ _______ A 79, 690 . 849 93, 900 5% .174 . 711 112, 200 3. 953 . 1227 . 660 120, 800 Q783 _____ ___ -- -- A 68, 650 . 845 81, 200 5% .174 . 707 97, 200 3. 953 .1227 . 656 104, 700 Q787__ __________ B 74, 960 . 690 108, 500 5% . 059 . 643 116, 700 1. 391 . 0146 . 599 125, 200 Q788 ____________ B 69, 660 . 694 100, 400 5% . 062 . 646 107, 900 1. 453 . 0160 . 600 116, 200 Q789 ______ _____ _ B 60, 100 . 695 86, 400 5% . 062 . 647 92, 800 1.453 .0160 . 601 100, 000
Q793 _____ _______ B 86, 580 . 884 97, 900 5% . 172 . 750 115, 300 3.888 . l187 . 697 124, 200 Q794 ___ __ __ _____ B 83, 970 . 898 93, 600 5% .177 . 758 110, 800 4. 018 .1267 . 708 118, 600 Q795 _____ ____ ___ B 69, 200 .891 77, 700 5% .169 . 758 91, 300 3. 828 .1150 • 704 98, 300
Q796 ___ __ __ ___ __ c 76, 480 . 794 96, 300 5% .059 • 747 102, 300 1. 391 . 0146 . 703 108,800 Q797 __ ___ __ _____ c 74, 350 . 794 93, 600 5% . 059 . 747 99, 400 1. 391 . 0146 . 703 105, 700
Q798 ______ ___ ___ c 74, 110 . 790 93, 800 5% .059 . 743 99, 700 1. 391 . 0146 . 699 106, 200 Q799 _____ _____ __ c 97, 570 . 871 112, 000 5% .062 . 822 1l8, 700 1. 453 . 0160 . 776 125, 700 Q8oo _____ __ _____ c 88, 890 . 870 102, 000 5% .062 .821 108, 200 1.453 . 0160 . 775 114, 600 Q80L ___ _______ c 82, 620 . 878 94, 100 5% .062 . 829 99, 700 1. 453 . 0160 . - 783 105, 400 Q802 ____ ________ c 93, 590 . 993 94, 300 5% .174 . 855 109, 400 3. 953 .1227 .804 n~:igg
Q803__ ___ _______ c 86, 850 . 995 87, 200 5% . 174 .857 101, 300 3. 9.53 .1227 .806 Q804 ___ ______ ___ c 76, 500 .980 78, 000 5% .169 . 847 90, 300 3. 828 .1150 . 793 96,500
Q805 _____ ___ __ __ c 120, 400 1.074 112, 000 5% . 169 . 941 128, 000 3.828 .1150 .887 135, 800 Q806-. ___ _______ c 109, 900 1.076 102, 300 5% .174 . 938 117, 300 3.953 .1227 . 887 123, 800 Q80L ___ ____ ___ c 98, 700 1.068 92,300 5% .169 . 925 106, 700 3. 828 .1150 . 871 113, 300
Q811 _____ _______
D 109, 400 .916 119, 500 5% . 062 .867 126, 300 1.453 . 0160 . 821 133, 300 Q812__ ____ -- ---- D 104, 200 .920 113, 300 5% . 059 . 874 119, 300 1.391 . 0146 .830 125, 500
Q813 ______ __ ____ D 81, 500 . 920 88, 600 5% .062 . 871 93, 600 1.453 . 0160 . 825 98, 800
Q823 ____ ________ E 90, 120 .854 105, 500 5% .062 . 805 112, 000 1.453 . 0160 . 7.59 118, 800
Q824 ______ ______ E 85, 710 . 851 100, 700 5% .062 . 802 106, 800 1. 453 . 0160 . 756 113, 300
Q825 ______ _____ E 77, 400 .848 91,300 5% .062 . 799 96, 900 1. 453 . 0160 . 753 102, 800
Q829 __________ __ E 102, 800 I. 046 98,300 5% . 169 . 913 112, 500 3. 828 .1150 .859 119, 700
Q830 __________ __ E 99, 100 I. 043 95, 000 5% .169 . 911 108, 800 3. 828 .1150 . 857 l15, 600
Q83!__ ___ _____ __ E 80, 400 1. 052 76, 500 5% .169 . 919 87, 500 3.828 .1150 .865 93,000 Q835.. __________ F 128, 400 1.088 118, 000 5% . 059 1. 041 123, 400 1.391 . 0146 .997 128, 800
Q836 __ __________ Q837 _________ ___ ]!' 127, 900 1.086 117, 800 5% . 062 1.037 123, 300 1.453 .0160 . 991 129, 100 Q84L ______ _____ ]!' 88, 800 1.080 82, 200 5% . 062 I. 031 86, 100 1.453 . 0160 . 985 90, 200 F 142, 300 1. 2'!4 110, 800 5% . 174 L 146 124, 300 3.953 . 1227 1. 095 130, 000
Q842 ____________ F 133, 300 1. 273 104, 700 5% . 174 1.135 117, 400 3.953 .1227 1. 084 123, 000
Q843 ___________ _ F 106, 900 1. 279 83, 600 5% .174 1.141 93, 700 3. 953 .1227 1. 090 98, 000
9
TABLE VI.-R series-Stiffener pitch = 4 inches-Number of stiffeners, 3-Test data and calculations
Thickness
Total Total Corrugation Stiffener
Speci- Type Average Failing area area Type
men of Weight area load Length Width sheet stiffeners af
no. section (pounds) (square (pounds) Stiffener Sheet (inch) (inch) inches) (square (square Pitch Depth Width Depth fail- (inch) (inch) inch) inch) (inch) (inch) (W- (D- ure
inches) inches)
--- ------ -------- --------------- - - -- ------ --
R856 .... c 2.108 o. 554 47, 600 0. 020 0. 015 13. 32 9. 55 0.143 0.411 H ,. R857 .... c 4.192 1 1% c . 550 46, 920 .020 .01 5 26. 63 9. 58 .144 . 406 H >• 1 1% c R858 .. .. c r.. 295 . 551 4r:, 100 .020 . 015 39. 93 9. 57 .144 . 407 H !,;, I l }ii G R859-. .. c 2. 770 . 727 79, 740 .030 .OJ!; 13. 32 n. 5.5 . 143 .!i84 >~ >s 1 1% c R86Q __ . c 5. 54i . i29 78, 740 .030 . 015 26. 58 !). 56 . 143 . 586 H i~ l 1% c R86L . . c 8.323 . 729 70, 150 . 030 . 015 39. 92 9. 56 . 143 . 586 ~2 >s 1 1% G R862. .. _ c 2. 237 . 587 57, 770 . 020 . 015:3 13. 32 9. 55 .146 . 441 H 'Yi • •v..2 1' Y.i2 c R863. ___ c 4. 493 . 589 54, 430 .020 . 015 26. 64 9. 57 . 144 . 445 ,~ h 6 "Y.!2 I' J.12 c R864. ___ c 6.812 . 596 54, 600 .020 . 015 39. 90 9. 55 . 143 . 453 H 'J.i s •v..2 l' >~2 G R865 .... c 3. 021 . 793 97, 400 . 030 . 0152 13. 31 9. 53 .145 . 648 H 'J.i o ·>~2 1 1 ~2 c R866. ___ c 6.025 . 793 90, 190 . 030 . 015 26. 61 9. 53 .143 . 650 H '!1 • •v..2 [I J.12 G R867 ___ c 9. 024 . 790 67, 700 . 030 . 015 39. 91 ~. 54 . 143 . 647 H 'Yi • •v..2 [I J.12 11 U874. ___ D 2. 451 . 623 61, 020 .020 . 015 13. 76 9.54 .143 .480 ,~ 'h°• •J.12 l' J.12 c R875 ___ ]) 4. 742 . 602 fiJ , 750 . 020 . 0145 27. 53 9. 54 .139 . 463 H 'Yi• •J.12 l' J.12 c 1{876 ___ _ ]) 7.408 . ll27 50, 500 .020 . 0152 41. 27 9. 52 . HI\ .482 Y.i 'Ylo •9'2 11H 2 0 R877 ____ ]) 3. 293 . 836 97, 440 . 030 .015 13. 75 9. 53 . 143 . 693 H 'Yt• •Y.i2 1• Y.i2 c R878 ___ ]) 6. 584 . 836 89, 310 . 030 . 015 27. 49 9. 52 . 14J . 693 H 'Vi• •Y.i2 [I Y.i2 G R879 ___ D 9. 8S8 . 837 71, 800 . 030 . 015 41. 2>1 9. 54 .143 . 694 ~ ~1G •Y.i2 l'>fa G R88L .. E 2. 347 . 587 45, 860 . 020 .Olfi 13. 99 9. 55 . 143 . 444 H 'Vio I H~ H R88L .. E 4. 696 . 585 48, 840 .. 020 . 015 28. 03 9. 57 . 144 . 441 H 'h° • 1 1)4 B R888. ___ E !i. 918 . 585 40, 350 . 020 . 0153 42. 02 9. 57 . 146 . 439 ~ 'Vi• I 1)4 G R889. ___ E 3. 277 . 815 87, 140 . 030 . 016 14. 04 9. 59 .154 . 661 ,, R89L .. E 6. 548 . 815 71, 130 . 030 . 016 28. 01 'h°• 1 H( B 9. 57 . 153 . 662 ~ 'Vi• 1 1)4 G R89L .. Jc 9.852 . 819 62, 050 . 030 .016 41.99 9. 57 . 153 . 666 ~ Yi• 1 H4 G R898 ____ ];' 2. 895 . 697 72, 350 .020 . 0155 14. 52 9. 57 .148 .549 H Yi• I 1)4 A R899. ___ F 5.803 . 699 62, 130 . 020 . 0153 29. 03 9. 56 . 146 . 553 >2 ')io 1 1)4 A R900 ___ F 8. 545 . 686 55, 950 . 020 . 0153 43. 52 9. 57 .14o . 540 H 'h°• 1 1)4 G R9QL_ __ F 4. 077 . 982 108, 900 . 030 . 0155 14. 51 9. 57 . 148 .834 H Ho 1 1)4 B R902_ ___ F 8.171 . 98\5 98, 700 . 030 . 0155 29. 01 9. 56 .148 . 837 J.2 Mo I I H G R903 ___ F 12.198 . 980 79, 60Q . 030 . 016 43. 49 9. 58 . 153 . 827 J.2 'h°• 1 IH G R9JQ ____ c 4.159 . 828 75, 75f) . 030 . 015 17. 58 9. 55 . 143 . 685 H >• I 1% c R9ll ____ c 8. 365 . 830 75, 010 . 030 . 015 35. 20 9. 54 . 143 . 687 )6 >• 1 1% c R9!2.. __ c 12. 522 . 830 73, 600 .Olla . 0153 52. 78 9. 55 . 146 . 684 >2 J.~ 1 1% I R913 ... . c 4. 576 . 908 89, 800 . 030 . 015 17. 62 9. 56 .143 . 765 ~ '!1 • • v..2 J2 )'.i2 c R9J4_ __ _ c 9.103 . 904 83, 290 . 030 . 0153 35. 22 9. 54 .146 . 758 H H o •>12 !2%2 c R9!5. ... c 13. 747 . 910 96, 700 . 030 .Oll.53 52. 83 9. 53 .146 . 764 H '!1 • •J.12 12%2 G R9J9 ___ D 4.850 . 955 96, 700 . 030 . 015 17. 78 9. 54 .143 . 812 H Ho ·~2 12%2 c R920. . . . D 9. 650 . 950 87, 180 . 030 . 015 35. 49 9.51 .143 . 807 H %6 •Y.i2 12%2 c R92L. . . D 14. 278 . 955 90, 100 . 030 . 0155 52. 28 9. 53 .148 . 807 J.2 ~1· 3)-12 J2 )'.i2 G R925. .. . E 4. 966 . 926 85, 660 . 030 . 0155 18. 74 9. 57 .148 . 778 H ')05 1 1% c R926 .... E 9. 996 . 932 83, 600 . 030 . 0155 37. 48 9. 58 .149 . 783 H '!1 • 1 1% H R927. ... E 14. 968 . 930 75, 200 . 030 . 016 56. 24 9. 54 .153 . 777 H H• 1 1% G R93J.. __ F 5. 970 1. 098 117, 100 . 030 . 0155 19. 01 9. 55 .148 . 950 H 'h°• 1 1% H R932 .... }' IL 943 I. 100 llO, 800 . 030 . 0155 38. 00 9. 56 .148 . 952 H ~1 6 1 1% G R933 .. .. F 17. 973 1. 103 95, 500 . 030 . 016 56. 99 9. 56 . 153 . 950 H 'h° • 1 1% G R940. .. . c 4. 577 . 888 91,000 . 030 . 0145 18. 02 9. 32 . 135 . 753 % J4 % 2).io I R94L. __ c 9. 155 . 888 89, 600 . 030 . 015 36. 03 9. 30 . 139 . 749 % J4 % 2).16 G R942.. __ c 13. 800 . 892 85, 000 . 030 . 0150 54. 03 9. 31 . 140 . 752 % H % 2).io G R94L .. c 4. 845 . 939 120, 600 . 030 . 0150 18. 01 9. 25 . 139 .800 % ~16 1 J.1• 2J.12 I R94L .. c 9. 638 . 935 111, 200 . 030 . 0150 36. 02 9. 25 . 139 . 796 % ~ . R945. ... c 14. 563 . 942 97, 500 . 030 . 0150 54. 02 9. 25 .139 'J.1• 2~2 I R958. ... F . 803 % ~1 6 'J.1• 2>~2 G 6. 054 I. 058 . 117, 500 . 030 . 016 20. 02 9. 33 .149 . 909 % H % 1% I R959 ____ F 12. 094 I. 058 110, 400 . 030 . 016 39. 98 9. 32 . 149 .909 % J4 % 1% G R960 .... F 18.159 I. 059 89, 100 . 030 . 016 60.00 9. 31 . 149 . 910 % H % ! ).ii G R96L. .. F 6. 382 1. 113 124, 500 . 030 . 0155 20. 02 9. 32 .144 . 969 % ~ . Jl962. ... }' 12. 789 1.118 115, 600 . 030 % l' )-12 I . 0155 40. 00 9. 30 .144 . 974 % ~ . Jl963 .. .. F 19. 298 1. 119 95, 200 . 030 . 0155 59. 96 % J2)-12 I 9. 31 . 144 . 975 % ~ . % ] 2)-12 G
10
TABLE VII.- R series-St(O'ener pilch=4 inches-Number of stiffeners, 3- Test data and calculationg
Method A
Average
Average failing
Type Failing area stress Width of Specimen no. of load (pounds sbeet act- Area of Total
section (pounds) (square per ing at sheet area
incb) square stiffener acting acting
incb) stress (square (square
(inches) incb) inch)
------- ---
R856 _____ ____ ___ c 47, 600 0.554 86, 000 4~8 0. 062 0. 473 R 857 ____ _______ c 46, 920 . 550 85, 200 4Hi . 062 . 468 R858 __________ __ c 46, 100 . 551 83, 600 4Ys . 062 . 469 R 859 ___________ _ c 79, 740 . 727 109, 500 4Hi . 062 . 646 R 860 __ __ ________ c 78, 740 . 729 108, 000 4!-i . 062 . 648 R86L ___ ____ __ _ c 70, 150 . 729 96, 200 4),1< . 062 . 648 R862 _________ __ c 57, 770 . 587 98, 300 4~2 . 062 . 503 R863 ___ __ _______ c 54, 430 . 589 92, 500 4~2 . 060 . 505 R861 ___ __ _______ c 54, 600 . 596 91, 600 4~2 .060 . 513 R865 ___ _________ c 97, 400 . 793 . 122, 800 4~12 . 06l . 709 R 866 _____ ____ __ _ c 90.190 . 793 113, 700 4~2 . 060 . 710 R867 _____ ______ _ c 67, 700 . 790 85, 700 4Vi2 .060 . 707 R874 ___ ______ __ _ D 61, 020 . 623 98, 000 4~2 .060 .540
R875 ___ __ -- ---- D 61, 750 . 602 102, 500 4~2 . 058 . 52! R876 _____ ___ ___ D 50. 500 . 627 80, 500 4~2 .061 . 543 R877 ____ ____ _ D 97, 440 . 806 116, 500 4~2 .060 . 753 R878__ ___ _____ :: D 89, 310 .836 106, 700 4''1!2 . 060 . 753 R879 _____ ___ __ _ D 71, 800 . 837 85, 700 4H2 . 060 . 754 R886 ___ ________ _ E 45, 860 . 587 78, 100 4Hi . 062 . 506 R887 __ __ __ ______ E 48, 840 . 585 3:,,500 4Hi . 062 . 503 R 888 _____ ____ ___ E 40, 350 . 585 69, 000 4Hi . 063 . 502
R&~9 ____ ____ __ -- E 87. 140 . 815 106, 900 4;i . 066 . 727 R890 ____ ________ E 71, 130 . 81.5 87, 300 4Hi . 066 . 728 R89!__ __ ________ E 62, 050 . 819 75, 700 4Hi .066 • 732 R898 ______ __ ___ _ F 72, 350 . 697 103, 700 4Hi .064 . 613 R899 ___ _________ F 62, ISO . 699 89, 000 4}{; . 063 . 616 R900 __ _________ F 55, 950 . 686 81, 600 4~s . 063 . 603 R90L ___ __ __ ___ F 108, 900 " 982 110, 900 4Hi .064 . 898 RP02 ____ ______ __ F 98, 700 . 985 100, 000 H8 .064 . 901 R903 ____ ________ F 79, 600 . 980 81, 200 4Hi . 066 .893 R910 __ __________ c 75, 750 .828 91, 500 4Hi . 062 . 747 R91L __________ c 75, 010 .830 90, 300 4>& . 062 . 749 R912 ___________ c 73, 600 .830 88, 700 4Hi . 063 . 747 R913 ____ _____ ___ c 89, 800 . 908 98, 900 4~2 . 060 . 825 R914 ____ ___ ___ _ , c 83, 290 .904 92, 100 4~2 .062 .820 R915 _____ _______ c 96, 700 . 910 106, 300 4~2 . 062 .826
R919 _____ ··---- - D 96, 700 .95.5 101, 200 4~2 . 060 . 872 R920 ____ _______ D 87, 180 . 950 91, 800 4~2 . 060 . 867 R92L_ __ ________ D 90, 100 . 955 94, 300 4~2 .063 . 870 R925 ___ _____ ____ E 85, 660 . 926 92, 500 4Hi . 064 . 842 R926 ___ ________ _ E 83, 600 . 932 89, 700 4H\ . 064 . 847 R927 ____ ______ _ E 75, 200 . 930 80, 900 4Hi . 066 .843 R%L_ __________ F 117, 100 1.098 106, 700 4Hi .064 1. 014 R932 ___ ______ __ _ F 110, 800 1.100 100, 800 4Hi . 064 1. 016 R933 ___________ _ F 95, 500 1. 10:! 86, 700 4Hi . 066 l. 016 R940 ____ _____ ___ c 91,000 .888 102, 500 3% .049 .802 R94L ____ _ , ___ _ c 89, 600 . 888 100,800 ::;:J . 051 .800 R942 ___ __ ___ ___ c 85, 000 . 892 95, 200 3% . 051 . 803 R943 ___ _________ c 120, 600 . 939 128, 400 3'Vio . 048 .848 R944 ___ _______ __ c 111, 200 . 935 118, 800 3'Vio . 048 .844 R945 __ __________ c 97, 500 . 942 103, 500 3~16 . 048 . 851 R958 __________ __ F 117, 500 1.058 111, 200 3% .054 . 963 R959 _______ ___ __ F 110,400 1. 058 104, 500 3% .054 . 963 R960 ________ ___ F 89, 100 1. 059 84, 100 3% . 054 . 964 R96L_ ___ _____ __ F 124, 500 1. 113 111, 800 3% . 052 1. 021 R962 ______ _____ F 11.5,600 1. 118 103,:!00 3% . 052 1. 026 R963 __ ___ __ _____ F 95, 200 I. 119 85, JOO 3% . 052 1. 027
Stiffener
failing Width of
stress sheet act- (pounds ing at per stiffener square stress inch) (inches)
100, flOO 1. 953
100, 300 1. 95:l
98, 300 I. 953
123, 400 1. 953
121, 600 1. 953
108, 300 J. 953
114, 800 I. 99l
107, 800 1. 953
106, 400 l. 953
137, 300 1. 978
127, 200 l. 95;,
95, 800 1. 95;;
113, 000 1. 953
118, 400 1.891
93, 000 1. 978
129, 300 I. 953
118, 600 1. 953
95, 200 1. 953
90, 600 l. 953
97, 100 "953
80, 300 1. P91
119, 800 2. 078
97, 700 2. 078
84, 700 2. 078
118, 000 2. 015
100. 800 1. 99!
92, 800 l. 901
121, 300 2. 015
109, 600 2. 015
89, 200 2. 078
101, ~00 1. 953
100, 200 1. 953
98, 500 1. 991
108, 800 1. 953
101, 600 l. 991
117, 200 1.991
110, 900 1. 953
100, 500 1. 953
103, 600 2. 015
101, 700 2. 015
98, 700 2. 015
89, 300 2. 078
115, 300 2. 015
109, 200 2. 015
94, 100 2. 078
113, 400 1. 891
112, 000 1. 953
105, 900 1. 95~
142. 300 l. 953
131, 700 I. 953
114, 500 1. 953
122, 000 2. 078
114, 700 2. 078
92, 400 2. 078
121, 900 2. 015
112, 700 2. 015
92,800 2. 015
Method B
Area of Total
sheet area
acting
(square
acting
(square
inch) inch)
---
0. 0293 0. 440
. 0293 . 4:,5
. 0293 . 436
. 0293 . 6l3
. 0293 . 6l5
. 0293 . 615
.0305 . 471
. 0293 .474
.0293 . 482
. 0301 • 678
. 02g3 . 679
. 0293 . 676
. 0293 . 509
.0274 . 490
.0301 • 512
.0293 . 722
. 0293 . 722
. 0293 . 723
. 0293 . 473
. 0293 . 470
. 0305 .464
. 0333 . 694
.0333 . 695
. 0:!33 . 699
. 0312 . 580
.0305 . 583
. 0305 . 570
. 0312 . 865
. 0312 .868
. 0333 . 860
.0293 . 714
. 0293 . 716
. 0305 . 714
. 0293 . 794
. 0305 . 788
. 0305 . 794
. 0293 . 841
. 0293 .836
. 0312 . 838
. 0312 .809
. 0312 . 814
. 0333 . 810
.0312 . 981
.0312 . 983
.0333 . 983
. 0274 . 780
. 0293 . 778
. 0293 . 781
.0293 .829
. 0293 . 825
. 0293 . 832
. 0333 . 942
. 0333 .942
. 033:l . 943
. 0312 1. 000
. 0312 1. 005
. 0312 1.006
Sti.f!ener
failing
stress
(pounds
per
square
inch)
---
108, 200
107, 800
105, 700
130, 200
128, 000
114, 000
122, 600
114, 800
113, 300
143, 700
132, 900
100, 300
120, 000
126, 000
98, 600
U5,000
123, 500
99, 300
97, 000
104,000
86, 100
125, 600
102, 400
88,800
124, 700
106, 600
98, 200
125, 900
113, 700
92, 600
106, 200
104, 700
103, 200
113, 200
105, 700
121, 800
114, 900
104, 300
107, 500
105, 900
102, 700
92, 800
119, 300
112, 700
97, 200
116, 700
115, 200
108, 800
145, 300
134,800
117, 200
124, 700
117, 300
94,500
124. 50 0
000
0
115,
94, 70
11
Width
--+--- '
pitch
Perspective of ilfpical .specirnen .
Reif!.forr::l.nr:;
strip
t
FIGURE 1.
All bend radii= t1
D
Specimens whose depth is less
th.a.n J"harJe onl'f one bead a.i
the midpoint of ihe depth "n:'
Sec;J;{r;m, ~1.jpe used ~n speci'merzs
of N series.
FIGURE 2.
w
p
T1fpe-A
Plain bent u:p sect~on
Type-C
Bent up section with
backplate. A1-Backplate
w
D .
t t1 Tgpe-E
Built-up section with
reinjorcin<J .strip~
12
Rein.forcing
strips
Tgpe-13
Bent up sedr.'on with rer.'n.forclng
strips. A+ Strips.
Tgpe-D
Bent up sectl.on. w~th back
pta..te a.nd rel.~jorcin9 strips
C-r Strips
T1fpe-F
Built up section with back
plate a.nd reinforcing strips.
£+Backplate
1 II II 11 II • . Sect ion t'fpes used i'n specimens of Q a.nd R Serles.
FIGURE 3.
13
FIGURE 4. F IGURE 5.
F IGURE 6. F IGURE 7 .
14
FIGURE 8. F IGURE 9.
FIGURE 10. FIGURE 11.
15
FIGURE 12. FIGURE 13.
FIGURE 14. FIGURE 15.
16
FIGURE 16. FIGURE 17.
FIGURE 18. FIGURE 19.
17
FIGURE 20. FIGURE 21.
F IGURE 22. FIGURE 23 .
FIGURE 24.-Compression test set-up.
19
FIGURE 25.- Specimen MC659 supporting 75,750 pounds-Type C failure.
0
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