REPORT ON STATISTICAL EVALUATION OF THE CREEP-RUPTURE PROPERTIES OF FOUR HEAT-RESISTANT ALLOYS IN SHEET FORM By A. I. Rush J. W. Freeman Project 2059 June 1, 1954 Aviation Panel of the A.SME-ASTM Joint Committee on the Effect of Temperature on the Properties of Metals

STATISTICAL EVALUATION OF THE CREEP-RUPTURE PROPERTIES OF FOUR HEAT-RESISTANT ALLOYS IN SHEET FORM The rapid increase in the use of materials at increasingly higher temperatures presents the design engineer with the problem of establishing reliable new design values. Each material is expected to have a range in properties which reflects normal production variations in chemical composition, processing conditions, and heat treatment. Thus, sound design values require establishment of the ranges in properties normally to be expected under commercial production conditions. This paper presents the results of a statistical evaluation of the range in creep-rupture properties of four sheet alloys as commercially produced. The data established were those Irimarily required by the aviation industry for very high-temperature sheet applications. The alloys were 18-8 Ti (AISI 321), 18-8 Cb-Ta (AISI Type 347), N155 (AMS 5532), and Inconel X (AMS 5542). Ten sheets of each alloys from different heats were included. Attempts were made to obtain samples from several producers. Tests were carried out to establish the stresses for rupture according to the following schedule. Temp (~F) Rupture Time (hours) Type Alloys 1200 20 80 300 321, 347, Inconel X 1350 20 80 300 321, 347, Inconel X, N155 1500 5 20 80 321, 347 1500 20 80 300 Inconel X, N155 1650 5 20 80 N155 In addition, the creep curves from the rupture tests were analyzed for deformations of 0. 2, 0.5, 1. 0, and 2. 0 percent as a function of time.

2 The investigation was sponsored by the Joint Committee of the ASME-ASTM on the Effect of Temperatures on the Properties of Metals. The program was formulated and supervised by the Aviation Panel of the Joint Committee. DESCRIPTION OF TEST MATERIAL The alloys were all furnished gratuitously by several producers as commercial material produced to the following specifications: Material Specification Condition Finish AISI 321 MIL-S-6721, comp. Ti annealed Commercial 2-D and pickled AISI 347 MIL-S-6721, comp. Cb-Ta annealed Commercial 2-D and pickled N155 AMS 5532 per AMS 5532 per AMS 5532 Inconel X AMS 5542 heat treated per AMS 5532 and aged The heat numbers, number of sources, chemical composition, and other descriptive material supplied by the manufacturers are given in Tables I through IV. PROCEDURE The general procedure was to sample each sheet according to a scheme designed to avoid misleading results from possible variations within the individual sheets. Tensile tests were run at room temperature to show normal variation in properties from sheet to sheet and within each

3 sheet. Rupture tests were made by estimating the stress required to give rupture at the intermediate time periods and then adjusting the stresses in subsequent tests to give rupture in the specified time periods. Creep curves, including stress-strain curves during loading, were established for the rupture tests. No means was available for reliably fastening extensometers to the gage lengths of the specimens during the rupture tests. For this reason, they were fastened to the shoulders of the specimens. This necessitated considerable work to establish reliable means of correcting for strain in the fillets and shoulders of the specimens. A good deal of care was taken to follow exact procedures as agreed upon with representatives of the Aviation Panel. Because these may influence the results somewhat, they are presented in some detail in the following sections. 1. Sampling Two methods of sectioning of the sheets were employed, depending upon whether the direction of rolling was parallel to the long or short dimensions of the sheet supplied for testing. The sampling procedures are shown in Figures 1 and 2. Both procedures provided for cutting the sheet in three equal sections from which specimens were obtained with the testing direction transverse to the rolling direction. Two tensile specimens were obtained from each sheet, one from the outside edge of the sheet and the other from the center. At least one specimen was obtained from each section for each stress-rupture testing temperature. When more than one specimen was taken from the same section, the strips were tested insofar as possible at the two extremes of the

4 stress range. That is, to avoid the possibility of obtaining a false slope to the stress - rupture time curve if a uniform variation existed across the sheet, the specimens from consecutive sections were not tested at consecutive stress increments. 2. Specimen Design The specimens used for the stress-rupture tests were 22 inches long and 1 inch wide in the shoulder area. The reduced section was 0. 500 inches wide by 2. 25 inches long and was located in the center of the 22-inch length. The fillet between the reduced section and shoulder area had a 1-inch radius. Holes 5/32 inches in diameter were drilled in the shoulder areas for the attachment of extensometers. Figure 3 is a sketch showing the dimensions of the specimens. The tensile test specimens were similar, except that they were 1-1/4 inches wide inthe shoulder area to provide a large cross section at the pins used to apply the load. 3. Machining The same machining procedure was employed for all specimens. The specimens were milled to not less than 1/32 inch of finish size on each side and then ground to finish size. Final grinding was done in the longitudinal direction, using a 46 grit, white borlon, medium hard wheel with a vitrified bond (Simond's Wheel WA 46-K5-V1). 4. Testing Procedure A. Tensile Testing Duplicate tensile tests were run. All tests were conducted with a free head-speed of 0. 05 inches per minute, and strain data were obtained

5 by means of an optical extensometer system. The stress-strain curves plotted from this data were used to establish yield strengths. B. Stress-Rupture Testing All stress-rupture tests were conducted in single units of the dead weight-beam loaded type, except when low stresses required the use of a direct load. The following procedure was used to bring the test specimens to temperature: (a) Specimens were set up in the testing units and the heat turned on at 4:00 pm, so as to bring the temperature within 50"F of the desired temperature by 5:00 pm. (b) The specimens were allowed to stand overnight, and the temperature raised to the test temperature between 8:00 am and 9:00 am the next day. (c) Final temperature adjustments were made so that the stress could be applied at 1:00 pm. (d) The temperature distribution along the length of the specimen, and the temperature variations with time were within the limits of ASTM Specification E85. Time-Elongation data were obtained by means of extensometers. Collars were fixed on the upper and lower shoulders of the specimens by means of pins inserted through holes drilled in the specimen shoulder. Extension rods were attached to the collars and extended out of the furnace. Rollers carrying a mirror were inserted between each pair of extension rods. As the specimen deformed, the mirrors were rotated, and the rotation measured by a scale reflected in the mirrors to a telescope. The

6 readings on both sides of the specimens were taken and averaged. The sensitivity of the extensometer system was three-millionths of an inch per inch in the 2-inch gage length. Figure 4 shows the type of extensometer used, as well as the method of attachment to the specimen. Inasmuch as the extensometers were attached to the shoulders of the specimen, the observed deformations included elongation in the fillet and a portion of the shoulder, as well as in the reduced section. Consequently, it was necessary to establish factors which would correct the total deformation observed to that occurring in the reduced section. That is, the total extension measurements were translated into percent elongation of an "effective gage length. " The effective gage length is the hypothetical gage length which would deform the same amount as the total deformation measured by the extensometers. Two effective gage lengths were determined: one for the loading portion of the creep-rupture tests, and the other for the creep data obtained after the load had been applied. This was necessary because the relations between stress and strain during loading are different than during creep. (1) On loading, the specimen length covered by the extensometer deforms elastically in accordance with the stresses existing in the gage length, fillets and shoulder lengths. (2) As the load increases past the proportional limit, if such occurs, a steadily increasing amount of the fillet area deforms plastically. The total elongation measured during this part of the test then becomes a function of the proportional limit, the stress-strain behavior past the proportional limit, and the stress pattern existing in thefillet. (3) After the load becomes constant, the entire specimen deforms plastically in accordance with the stress - creep rate relationship for the

7 material and temperature. Therefore, the elongation measured during this period is a function of the stress - creep rate relationship and the stress pattern existing between the points of attachment of the extensometer. The effective gage length for the loading portion of the creep test was determined at room temperature by several tests run on specimens using both SR4 strain gages applied to the reduced section and the mechanical extensometers attached to the shoulders. The SR4 gages covered a 1-inch length of the reduced section and it was assumed that they gave accurate stress-strain data for values up to 0. 5 percent strain. The stress-strain data obtained from the mechanical extensometers were then adjusted by the use of a suitable correction factor to agree with the data from the SR4 gages. The continued use of this factor at stresses over the elastic limit resulted in less indicated deformationthan that shown by the SR4 gages. However, in the rupture test, the stresses either did not exceed the proportional limit or so far exceeded the elastic limit that deformations in excess of those of interest were obtained. Therefore it is believed that the deviation beyond the elastic limit did not significantly affect the design data. The correction factor was expressed in terms of the effective gage length previously defined. Furthermore, the effective gage length calculated on the basis of the stress distribution in the reduced section, shoulder radius, and shoulders was found to agree remarkably well with the experimental value. Several independent checks were conducted to determine the effective gage length for creep in the rupture test. Specimens were gage marked in a number of places in both the reduced sections and shoulder areas and carefully measured to 0. 0001-inch in the Gage Laboratory of the

8 Production Engineering Department before and after creep testing. The specimens used for this purpose covered a range of temperatures, stresses, creep rates, and materials. From these data, together with the extensometer readings obtained during the tests, an effective gage length was calculated. In addition, the effective gage length was calculated on the basis of stress distribution and the integration of creep rates in the entire section between the points of attachment of the extensometers. The values obtained for the effective gage length by these calculations agreed exceptionally well with those determined experimentally, as shown in the table on the following page. RESULTS Tensile Properties at Room Temperature The results of the tensile tests are given in Tables V to VIII. It will be noted that tensile properties were uniform. The most notable exception was Inconel X, Heat Y4474X, which had abnormally low strength. If Heat Y4474X were excluded from the values for the ranges reported in Table VII, the low side of the tensile strength range would have been 170, 000 psi, instead of the 156,600 psi shown. The other strength values were proportionately low for this heat. The duplicate specimens all agreed well in properties in every case, indicating no large variations within individual sheets.

Period Temp Stress Duration Total Minimum Effective Gage Length of Test Material of Test Deformation Creep Rate (OF) (psi) (hours)(%)__ (%/hour) Experimental Calculated Loading 321 Room 46,500 0.705 — 3.68 3.78 321 Room 41,000 -0.595 3.68 3.78 347 Room 43,500 — 0.615 3.68 3.78 Creep N155 1500 14,000 198 1.5 0.0055 2.71 2.61 Creep 321 1200 22,000 31 5.5 0.165 2.78 2.70 1500 8,000 17 1.7 0.165 3.06 2.90 Creep 347 1200 20,000 700 0.68 0.000624 2.81 2.70 s0

10 Stress-Rupture Properties The results of the individual stress-rupture tests are presented in Tables IX to XII, and are plotted on log-stress log -time coordinates in Figures 5 to 8. From these data the stresses for rupture in the specified times were obtained and are given in Tables XIII to XVI. Figures 9 to 12 show the ranges in these stresses as a function of temperature. The approximate ranges in elongations for fracture are also included in the figures. Three or four tests were run on each sheet for each temperature and a stress - rupture curve plotted. The stresses reported were obtained by interpolation on the stress - rupture time curves. In most cases, the stresses were adjusted so that the actual test times were not greatly different from those specified. In conducting the tests, it was not found possible to test all heats of a given alloy at the same stresses. This was due to the spread in rupture times for a given stress being too wide to enable proper establishment of the specified rupture times. After one test point was available, the stresses were adjusted to give fracture times near those specified. For instance, for N155, the spread in rupture times for the average stress for fracture in 80 hours at 1350~F was 55 to 100 hours. This range is wider than was specified for the investigation. Since N155 alloy gave the least variation in rupture times, the other materials had considerably wider variations in rupture times at a given stress. Several more tests would have been required for each rupture curve to have run tests on all heats at common stresses and also have established the specified rupture times. When the investigation was initiated, it was believed possible that the number of tests required could be reduced considerably by the use

11 of a time-temperature parameter for correlating stress-rupture data. (1) However, as the work progressed, it became apparent that the data did not fit a single stress-parameter curve sufficiently well to predict the strength of one heat upon the curve obtained from another heat. The individual test points for each alloy are plotted on stress-parameter coordinates in Figures 13 to 16. The time-temperature parameter employed was that developed by Miller and Larson where Parameter = T (C + log t). Temperature, T, is expressed in ~R; the time, t, in hours; and the value for the constant, C, is usually taken as 20. It was observed that changing the value of C resulted in better agreement for the values obtained from a single heat, but at the same time increased the disagreement for other heats. However, it is apparent from Figures 13 through 16 that the agreement in rupture strengths between the various heats was not sufficient to warrant its use in the determination of the range in rupture strengths for this investigation from a master curve established from a limited number of heats. It is likewise apparent that using a limited number of tests on each heat to establish a curve would not have been reliable. Total Deformation Strengths The available data for total deformations of 0. 2, 0. 5, 1. 0, and 2.0 percent in 1, 5, 20, 80, and 300 hours are given in Tables XIII through XVI. Where the data are sufficiently complete, the ranges are shown as a function of temperature in Figures 17 through 22. To obtain these data, the creep curve for each rupture test was plotted. The available times for (1) F. R. Larson and James Miller. "A Time-Temperature Relationship for Rupture and Creep Stresses." Trans. of ASME, Vol. 74, No. 5, July 1952.

12 the total deformations given above were obtained from these curves, Tables IX through XII. Curves were then plotted for stress versus the time for these total elongations for each test temperature on each heat. Values were then interpolated for the stresses for deformations in 1, 5, 20, 80, and 300 hours, depending on what data were available. Figures 23 through 26 illustrate the typical design curves obtained for one heat of each of the four alloys tested. The deformations reported are the total deformations from loading and creep. Some values were not obtained for the following reasons: (1) deformation during loading exceeded the desired values; (2) the total deformation exceeded those of interest in much less time than 300 hours; (3) in many cases creep rates were so high that deformations of interest were exceeded in less than 1 hour; (4) the total extension to fracture was less than 2 percent. Statistical Evaluation The tensile and stress-rupture data were analyzed statistically insofar as it was considered legitimate from the data available. The range, average, and standard deviation were determined for each alloy for the tensile strength, yield strength, proportional limit, and elongation values obtained from the tensile tests. These values are shown in Table XVII, together with the maximum difference in properties observed for one heat of the alloy. Similar values, range, average, and standard deviation, were obtained for all the stress-rupture strength data and for total deformation data where it was believed that sufficient data were available to warrant

13 statistical treatment. These values are given in Tables XVIII through XXI, together with the number of heats used in the calculation and the spread in values obtained by using the average plus or minus three times the standard deviation. In general, the data appeared to follow a rather normal frequency distribution and the agreement between the actual range in values determined and the probable range estimated by the average plus or minus three times the standard deviation was fairly good. Thus it might be expected that the samples was representative of the universe, although a much larger sample would be necesssary to substantiate this statement. For the tensile data, the major exception to this statement was the properties of the Inconel X sheet. The estimated range indicated that considerably higher strengths might be expected than were actually obtained. The agreement between the actual and estimated ranges in rupture strengths was quite good, although the estimated range for Inconel X indicated that heats with considerably higher and lower strengths than actually were obtained might be expected, especially at 1200~ and 1350~F. The statistical analysis of the total deformation strengths showed good agreement between actual and estimated ranges when sufficient data were available. However, it should be recognized that the heats for which no values were reported fall outside of the reported ranges and that the actual range in strength would be greater if sufficient data were available to establish these points. It should be emphasized that the statistical evaluation is based on rupture and total deformation strengths obtained from a plot of stress against time for rupture or given total deformation, and that the values obtained from such plots are subject to statistical variation in themselves.

14 That is, three to five tests run at a given temperature under different stresses were used to establish the stress-rupture or total deformation strengths, and since some scatter was observed for these points, the individual strengths for a single heat are subject to a plus or minus variation. However, since onlye three to five tests were run at each temperature and since these tests were obtained from somewhat widely spread locations within a single sheet, it was not thought feasible to attempt a statistical analysis of each heat. Furthermore, the ranges in stress-rupture strengths obtained from the stress-parameter curves of Figures 13 through 16 where all the individual points are plotted were only slightly greater than those obtained using the values taken from the individual rupture strengths. DISCUSSION Data are presented on the ranges in rupture and total deformation strengths of commercially produced sheet of 18-8 Ti (Type 321), 18-8 Cb + Ta (Type 347), N155 and Inconel X alloys for three time periods at three temperatures. Sample sheets from 10 separate heats of each alloy were used. In general, these data represent a more complete survey of the high-temperature properties of a given product than is usually available. The additional statistical analysis shows designers rather completely what to expect from the products. The reasons for the range in properties are not well established. The high-temperature properties of the alloys are known to be influenced by heat-treating temperatures, cold work, and variations in composition. Most studies of variability also indicate that differences arise from work

15 ing conditions prior to final heat treatment and from unidentified heat to heat variations. In general, the interrelations of these variables make it very difficult to establish specific causes. For these reasons, correlations between properties and compositions or tensile properties were not carried out. Any trends which might be indicated would have to be verified under more closely controlled conditions than were the case for this study. In general, where test material was obtained from more than one source, the sheets from one source tended to show properties which grouped more closely than the total spread. This would be expected for an established practice in one plant. All of the sheets coming from one producer quite certainly explains the small spread in properties for N155 alloy. On the other hand, all Inconel X sheets were also made by one producer. Inconel X, however, is dependent on precipitation of compounds of nickel with Al + Ti for its high strength. Alloys exhibiting such precipitation reactions might be expected to be considerably more sensitive to prior history than the other alloys. Heat treatments of the other alloys mainly dissolve precipitated carbides and remove cold work. It will be noted that Inconel X, Heat Y4474X, which had the low tensile strength at room temperature had about average properties at 1200~F, and was on the high side of the range at 1500 F. Due to space limitations, the actual test data are not included. In general, quite good stress - rupture time curves were obtained. There was, however, some scatter which appeared to be related to slight variations in specimens taken from the different locations in the sheets. The stress - rupture time curves were not parallel to one another, but were at varying angles. This would be expected for the several possible metallurgical variations affecting the properties. The distinct

16 nature of the individual stress - rupture time curves indicated metallurgical variation as the responsible cause of the spread in data, and not sampling or testing variables. The properties at high temperatures are expressed in every case as the variation in stress for rupture in a given time. It should be recognized, however, that the variation in time for rupture at a fixed stress was considerable. As mentioned previously in the case of least scatter, N155, rupture times at 1350~F would have varied from 55 to 100 hours under the average stress for rupture in 80 hours. In a more extreme case, that of Inconel X tested at 1200 F, the average stress for rupture in 80 hours gave times from 24 to 350 hours. This condition arises from the rather flat slope of the usual log-log stress - rupture time curves. Furthermore, the variation between specimens from an individual sheet run at constant stress would have been considerable, even though the average stress - rupture time curves were quite good.

TABLE I DESCRIPTION OF 18-8 TI (AISI TYPE 321) SHEET MATERIALS Chemical Composition (%) Gauge Supplier Heat No. C Mn P S Si Cu Ni Cr Ti Mo (in.) B R10356.042 1.44.027.009.57 - 9.49 17.41.65 -.040 B E02326.053 1.73.026.012.58 - 9.76 18.01.49 -.040 D E1880') -- - - -- -- -- -- --.040 C X25677.07 1.65.022..006.58 -- 10.43 17.84.55 -.040 D E41024(1) - - - - -- - -- -- - -.040 A 627967.078 1.33.025.009..34.27 9.98 17.75.57 -.048 B R30409.035 1.50.030.015.66 - 9.36 17.72.50 -.040 D E1869(1) -- - -- - -- -- - -- -- -.040 C X46099.06 1.56.021.005.84.24 10.21 17.76.49.13.035/.045 C X1 3043.05 1.43.029.005.94.24 10.56 17.56.46.15.035/.045 (1) Surface finish and composition not reported -- all other reported to have 2D finish.

TABLE II DESCRIPTION OF 18-8 CB-TA (AISI TYPE 347) SHEET MATERIALS Chemical Composition (%)___ _ Gauge Supplier Heat No. CS Mn P S 51 Cu Ni Cr TaTa Cb o (in.) A 620809.08 1.89.026.010.80.14 10.42 17.66.96 - -- -.040/.05 A 620813.076 1.78.024.010.53.16 10.34 17.92.77 -- - -.040/.050 A 636862.064 1.89.025.010.50.20 10.76 17.60.71 -- -.040/.050 D E40470.07 1.68.018.017.80.10 10.44 17.55 -.25.57.12.040 D E41286.06 1,52.033.021.57.16 10.37 17.55 -.13.67.14.040 D E41887.05 1.67.028.019.98.18 10.36 17.69.- 13.62.24.040 D E41737.05 1.88.024.016.62.15 10.33 17.68 --.10.63.18.031 C 7X7935.07 1.40.030.018.45.24 10.29 18, 49 -- -.76.15.035/.045 C X25788.07 1.83.016.005.73.26 11.91 17.68 - -.94 -.035/.045 C 3X0005(1).04 1.58.018.020.39.06 11.40 18.24 - -.62.02.035/.045 (1) 2B finish - all others 2 D finish.

TABLE III DESCRIPTION OF INCONEL X (AMS 5542) SHEET MATERIALS Gauge Supplier Heat No. C Mn S Si Cu Ni Cr Al Ti Cb Fe (in.) E Y4474X.05.57.007.36.07 73,.67 14.70.84 2.49.53 6.70.043 E Y3166X.04.54.007.36.03 73.07 14.73.80 2.38 1.02 6.94.043 E Y4602X.04.57.007.44.06 72.56 14.88.90 2.69.90 6.97.043 E Y4860X.03.50.007.30.02 73.46 14.66.88 2.59.83 6.70.043 E Y4512X.04.57.007.33.02 73.16 14.78.79 2.44 1.03 6.81.043 E Y4511X.03.56.007.31.02 73.25 14.71,77 2.35 1.09 6.88.043 E Y4847X.03.55.007.37.04 73.34 15.14.76 2.39.77 6.68.043 E Y4984X.03.54.007.39.16 72.96 14.93.85 2.57.88 6.66.043 E 253X.03.75.007.31.05 72.24 15.31.78 2.65,83 7.02.045

TABLE IV DESCRIPTION OF N155 (AMS 5532) SHEET MATERIALS Heat Chemical Composition (%) Gauge Supplier No. C Mn P S Si Ni Cr Co Cb Ta CbITa W Mo N2 (in.) F M624.11 1.45.028.013.41 20.08 21.20 20.05 --.84 2.40 3.08.12.044 F M206.08 1.32.022.020.50 19.72 21.52 19.81.66.23.89 2.37 3.22.12.042 F M208.10 1.50.023.018.50 19.26 21.66 19.37.80.25 1.05 2.34 3. 17 14.042 F M207.10 1.47.021.015.50 19.88 21.49 19.49.79.23 1.02 2.53 3.28.11,042 F M733.10 1.39.020.015.53 20.18 20.83 20.17 - -.81 2.46 2.98.11.050 F M737.12 1.69.030.015.46 20.36 21.17 19.52.- 81 2.25 3.06.11.050 F M732.11 1.27.026.015.53 20.04 21.08 20.26 -- -.82 2.38 2.96.10.050 F M731.13 1.36.021.014.49 19.75 20.78 19.38 - --.79 2.42 2.84.10.050 F M726.12 1.62.020.012.50 19.37 21.74 20.25 -- -.81 2.43 3.08.11.050 F M730.10 1.52.020.016.42 20.12 20.78 19.05 -- -.76 2.52 2.96.10.050

TABLE V ROOM TEMPERATURE TENSILE DATA FROM- TYPE 32.1 SHEET Tensile Offset Yield Strength Proportional Elongation Heat No. Strength psi) Limit (psi) 0. 1% 0. 2%0 (psi) (% in 2 in.) R10356 85,700 31,000 34,000 15,000 62.5 85,600 31,500 36,000 15,000 63.0 E02326 90,600 31,000 35,000 15,000 67.0 90,500 33,000 36,000 16,000 68.4 E1880 89,200 33,500 36,000 20,000 67.4 88,800 30,000 33,000 14,500 62.0 X25677 92,800 32,000 35,500 14,000 58.5 90,200 31,500 34,500 16,000 62.5 E41024 90,800 27,500 30,000 14,500 74.4 89,600 32,000 33,500 22,000 74.7 627967 81,500 34,500 37,000 14,000 64.5 81,600 36,500 39,000 15,500 66.0 R30409 85,400 28,500 30,500 15,500 66.5 85,700 27,500 31,500 19,000 65.0 E1869 90,300 31,000 34,500 15,000 69.5 86,300 31,000 34,500 16,500 68.5 X46099 92,200 43,500 45,500 20,000 51.0 90,600 40,000 43,000 20,000 54.5 X13043 92,700 39,000 41,500 14,000 60.0 90,800 34,500 39,500 14,000 62.5 Range 81,500/ 27,500/ 30,000/ 14,000/ 51.0/ 92,800 43,500 45,500 22,000 74.7 Average 88,550 32,900 36,000 16,300 64.4 Standard 3,380 3,960 3,910 2,440 5.65 Deviation

TABLE VI ROOM TEMPERATURE TENSILE DATA FROM TYPE 347 SHEET Tensile Offset Yield Strength Proportional Elongation Heat No. Strength (psi) Limit (psi) 0. 1% 0. 2% (psi) (% in 2 in.) 620813 94,000 38,500 42,000 16,000 60.0 94,900 38,000 42,000 14,000 61.5 636862 93,400 39,000 42,000 15,000 60.5 92,400 39,000 41,500 16,000 64.5 E40470 94,000 35,500 39,500 18,000 61.5 93,300 36,500 41,000 20,000 58.0 E41286 88,200 36,000 39,500 18,000 61.5 91,200 34,500 39,000 17,000 61.0 E41887 102,800 40,500 42,500 25,000 63.0 100,000 45,000 48,500 28,000 57.5 E41737 93,600 42,500 44,000 28,000 59.5 93,200 32,500 35,500 19,000 60.0 7X7935 99,100 42,500 47,500 19,000 52.0 97,100 42,500 46,000 19,000 55.5 X25788 97,800 46,500 51,500 21,000 47.0 95,600 51,000 54,000 21,000 51.5 3X0005 87,500 39,000 41,000 20,000 66.0 90,500 36,500 40,000 19,000 63.0 Range 87,500/ 32,500/ 35,500/ 14,000/ 51.5/ 102,000 51,000 54,000 28,000 64.5 Average 94,400 39,800 43,300 19,800 59.1 Standard 3,840 4,490 4,540 3,850 4.74 Deviation

TABLE VII ROOM TEMPERATURE TENSILE DATA FROM INCONEL X SHEET Tensile Offset Yield Strength Proportional Elongation Heat No. Strength (psi) Limit (psi) 0. 1% 02% (psi) (% in 2 in.) Y4474X 156,500 99,500 102,000 76,500 32.0 156,500 100,000 105,000 77,000 30.0 Y3166X 170,700 114,000 118,000 92,000 26.0 170,700 113,000 115,000 90,000 31.0 Y4602X 179,300 122,000 126,000 91,000 25.0 177,700 117,000 122,500 92,000 26.0 Y4860X 170,600 115,000 119,000 89,000 31.0 172,000 118,000 121,000 89,000 27.5 Y4512X 175,400 118,000 122,000 89,000 28.5 176,800 119,000 1-24,500 87,000 29.5 Y4511X 174,700 118,000 120,500 85,000 31.0 171,800 114,500 118,000 86,000 30.5 Y4847X 170,700 114,750 118,000 85,000 29.5 174,200 120,250 124,000 90,000 30.0 Y4984X 183,800 128,000 131,000 109,000 24.0 182,500 128,000 132,000 102,000 23.5 253X 185,800 132,500 136,000 110,000 24.0 184,500 130,000 135,000 100,000 24.0 Range 156,500/ 99,500/ 102,000/ 76,500/ 23.5/ 185,800 132,500 136,000 110,000 32.0 Average 174,000 118,000 121,500 91,100 28.0 Standard 7,900 8,550 8,725 8,890 2.86 Deviation

TABLE VIII ROOM TEMPERATURE TENSILE DATA FROM N-155 SHEET Tensile Offset Yield Strength Proportional Elongation Heat No. Strength (psi) Limit ______ (psi) 0. 1% 0. 2% (psi) (% in 2 in.) M624 117,700 50,400 55,400 20,000 56.0 117,200 51,500 56,800 29,000 55.5 M206 117,700 48,000 56,600 18,000 52.0 118,300 47,900 56,500 19,000 52.5 M208 120,200 58,000 64,500 26,000 52.5 119,700 51,800 59,500 22,000 53.5 M207 118,200 53,500 57,700 28,000 53, 6 119,400 54,700 61,600 26,000 53.6 M733 120,000 54,500 61,800 25,000 54.0 120,200 51,500 59,500 20,000 52.0 M737 120,500 55,000 59,500 27,000 57.5 121,200 53,000 60,000 20,000 54.5 M732 119,600 53,000 60,500 22,000 54.0 119,500 54,000 60,600 22,500 55.0 M731 118,200 51,200 61,500 17,000 51.5 120,500 52,000 62,600 17,000 52.5 M726 120,200 51,500 58,800 20,000 54.0 119,300 50,000 57,800 17,500 55.0 M730 116,800 53,000 59,800 17,500 54.5 116,600 50,50Q 60,000 18,000 53.0 Range 116,600/ 47,900/ 55,400/ 17,000/ 51.5/ 121,200 58,000 64,500 29,000 57.5 Average 119,050 52,250 59,550 21,575 53.8 Standard 1,320 2,340 2,230 3,850 1.47 Deviation

TABLE IX STRESS-RUPTURE AND TOTAL DEFORMATION DATA FOR TEN HEATS OF TYPE 321 SHEET TESTED AT 1200~, 1350', AND 1500~F Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. men(a) Time on Loading (hours) Location ( ~F (psi) (hours) (% in 2 in.) (in./in.) 0.2 0. 5 1.0 2.0 R10356 3 1200 36,000 11.8 17.5 >. 02 b b b b 1 28,500 80.0 34.5.00910 b b 0.2 31.6 2 22,500 338.3 31.0.00154 5 61.5 86 119 3 1350 18,000 35.5 23.5.0012 0.6 3.0 6.0 13.0 1 14,500 83.5 — (e) 00097 1.6 7.5 16.6 34.6 2 10,500 597.8 20.5.00064 14 48 113 195 1 1500 11,500 7.6 24.0.00105 0.1 0.5 1.0 1.7 3 10,000 23.3 25.0.00086 0.4 1.5 3.1 5.0 2 7,000 85.3 25.0.00051 2.5 6.5 12.5 25 E02326 2 1200 37,500 9.8 10.5,. 040 b b b b 1 27,000 95.5 11.0.0073 b b 0.5 44 3 22,000 308.1 13.0.00117 2 45 110 176 3 1350 16,000 33.3 7.0.00097 1.5 7.5 14 21.5 2 13,000 128.0 15. (e).00070 15 30 44 63 1 11,200 191.0 11.5.00060 13 31.5 49 78 3 9,400 584.0 8.5.00050 27 62 114 203 1 1500 12,500 6.1 25.5.00093 0.1 0.5 1.1 2 2 8,800 30.4 14.5(e).00073 0.8 2.6 5.0 8.7 3 7,400 54.9 3.6(c).00061 1.3 5.0 10.5 19.2 E1880 2 1200 34,000 21.5 15.5. 0220 b b b b 1 29,000 55.6 12.0.0137 b b b 1.5 3 22,000 515.0 23.5.00150 0.5 55 125 214 3 1350 21,000 23.0 26.5.00134 0.1 0.4 1.4 5.8 2 16,000 106.2 14.5.00092 2.5 14 24 41 1 13,000 314.0 12.0.00072 7 28 62 122 3 1500 15,000 4.5 26.0.00152 -- 0.15 0.4 1.2 1 12,000 14.7 16.0.00082 0.3 1.2 2.6 4.5 3 8,200 91. 5 12.0.00051 2.5 7.6 16 29 1 6,800 199. 3 7.0.00045 4 17.5 38 72.5 X25677 3 1200 36,000 10.2 11.5,. 024 b b b b 1 28,500 84.4 24.0.0080 b b 0.2 24 2 23,000 337.2 22.0.00175 0.5 22 70 127 3 1350 19,000 31.2 26.0.00105 0.4 1.7 3.8 8.9 1 14,500 114.9 17.5(c).00070 6 20 32.5 45 2 12,000 372.0 14.0.00056 18 40 73 105 2 1500 14,000 2.9 31.0.00134 -- 0.05 -0.2 -0.4 1 11,500 20.3 28.5.00078 0.1 0.4 0.9 1.6 3 7,500 60.7 30.5.00056 2 7 15 22 E41024 2 1200 37,500 15.5 12.0,. 04 b b b b 1 28,500 151.2 10.0.016 b b b 1 3 25,500 249.5 10.5.0117 b b b 100 2 1350 23,000 15 10.5.00508 b b 0.05 0.7 1 19,000 84.6 7.0.00159 -- 0.5 3 42 3 17,500 131.9 14.0.00094 2 22 59 88 2 15,500 173.8 8.5.00083 4 39 88 125 3 1500 14,000 4.2 27.0.00150 -- 0.1 0.3 0.6 1 11,500 16.9 14.0.00111 0.5 1.7 3.9 8 2 8,000 151.7 6.0.00068 6 21 43 78

TABLE IX, Continued Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. men(a) Time on Loading (hours) Location (F) (psi) (hours) (% in 2 in.) (in. /in. ) 0 0.5 1.0 2.0 627967 3 1200 33,000 17.1 10.5,,.02 b b b b 1 28,500 57.5 9. 5(d).0083 b b 0.5 25 2 22,000 342.0 11.0.00138 30 67 97 146 3 1350 17,000 45.4 9.5.00105 - 1 1, 500 151.3 9.0.00082 3.5 17 42 88 2 13,000 293.5 9.0.00071 16 56 100 176 1500 13,000 8.0 21.5.0011 0.2 1.0 2 3.0 1 11,500 15.5 21.0.00092 0.3 1.0 2 4.1 3 7,500 124.1 12.0.00062 4 21 50 100 R30409 3 1200 35,000 17.6 12.0,. 04 b b b b 1 28,500 64.2 5.5.0132 b b b 13 2 22,000 294.5 18.5.00490 b -- 73 143 3 1350 19,000 27.7 18.5.00130 -- 0.3 1.2 7.4 1 14,500 112.7 16.0.00078 6.5 19.5 29 45 2 12,000 240.0 10.0.00067 13.5 36 67 126 1 1500 11,500 7.2 12.5(d).00090 -- 0.2 0.5 1.3 3 9,400 43.8 13.5.00076 1.4 5 9.2 15.2 ~~2 77,000 97.7 6.5(d).00055 3.6 10.5 18 30 E1869 3 1200 35,500 21.3 11.5,. 02 b b b b 1 28,500 127.0 14.0.0087 b b 0.5 63 2 25,000 240.4 9.5.00413 b 1 65 122 2 1350 21,000 18.4 27.0.00161 -- -- -- -- 3 17,500 84.9 22.0.00106 2.5 10 17 30 1 14,500 219.5 8.5.00085 8 28 62 112 2 1500 14,000 9.6 25.0. 00109 0.1 0.5 1.2 2. 3 1 11,500 31.8 16.5(d).00070 0.8 2.7 5.9 9.6 3 9,500 49.7 18.5.00060 2.5 8 16.5 29.5 X46099 3 1200 34,000 8.0 21.5.00979 b b -- 0.1 1 28,500 45.9 35.0.00177 -- 0.7 4.0 7.5 2 21,000 316.3 17.5.00115 3 27 49 80 1 1350 22,500 6.9 18.0.00170 -- -- - 2 17,000 31.0 33.0.00124 0.2 0.8 2.7 5.2 3 14,000 116.9 16.5.00090 1.2 4.8 10.8 23 1 12,500 160.9 14.5.00085 2 7.2 19 44 1 1500 11,500 11.0 28.5.00125 -- 0.2 0.6 1.4 3 9,400 23.4 17.0.00108 0.2 0.6 1.6 3.6 2 7,200 84.6 18.0.00066 1.4 4. C 9.0 18.0 X13043 1 1200 28,500 25.6 17.5.00355 b -- 0.2 1.2 3 23,000 121.8 10.0.00137 0.5 3.5 11 29 2 20,000 268.5 17.0.00108 3 14 35 70 1 1350 17,000 25.5 29.0.00131 0.2 1.4 4.4 10.5 2 13,500 110.6 20.0.00085 1.4 6.4 14.3 26.0 3 11,000 242.2 13.0.00075 3.0 10.7 23 54.0 1 1500 11,500 10.3 26.0.00125 0.1 0.6 1 2 3 9,000 22.9 25.0.00073 0.3 1 2.4 4.9 2 6,600 130.1 30.0.00055 1.4 4.3 9.2 22 (a) Number identifies third of sheet from which specimen was taken. (b) Exceeded indicated deformation on loading. (c) Fractured through gage mark. (d) Fractured outside of gage marks. (e) Fractured at two places.

TABLE X STRESS-RUPTURE AND TOTAL DEFORMATION DATA FOR TEN HEATS OF TYPE 347 SHEET TESTED AT 1200~, 1350~, AND 1500~F Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. men(a) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in. /in.) 0.2 0.5 1.0 2.0 620809 3 1200 37,000 31.0 10.0.0356 b b b b 1 32,500 61.9 6.0.0158 b b b 0.8 2 28,500 281.4 7. 0.0100 b b b 52 3 1350 22,000 25.3 18.5.00195 -- 0.2 0.7 5.1 1 18,000 83.6 14.0.00118 0. 7 11 25 44 2 14,000 288.5 25.0.00080 8 31 76 114 3 1500 12,200 12.0 28.0.0011 -- 0.2 0.7 1.7 1 11,500 19.6 33.0.00085 0. 2 0.6 1.5 2.9 2 8,200 85.6 18.5.00058 2.5 7.5 14 23 620813 1 1200 38,000 24.8 12.5(c).0240 b b b b 3 32,000 132.1 16.5.0118 b b b 2 2 28,500 381.4 9. O(c).00400 b -- 10 137 2 1350 26,000 11.4 23.0.00625 b b -- 0.3 1 17,500 134.8 26.0.00111 1 5 25 51 3 15,500 221.8 17.0(c).00088 7 40 77 109 2 1500 15,000 5.2 29.0.00123 -- -- 0.1 0. 3 1 12,000 16.6 40.0.00091 -- -- 0.5 1.2 3 7,600 118.1 20.5.00045 5 12 20 32.5 636862 1 1200 36,000 37.5 14.5.0220 b b b b 2 32,000 74. 1 11.0.0133 b b b 1.5 3 28,000 268.0 10.5.0100 b b b 44 1 1350 20,500 42.z 21.5.00172 -- 0.4 1.5 10 2 16,500 125.5 21.2.00085 1.3 12 28 46.5 3 14,000 237.0 30.5.00078 6 36 68 96 1 1500 16,000 1.4 35. 0.00264 b 3 13,000 11.1 42.5.00118 -- 0.2 0.5 1.1 2 9,700 36. 6 18.5.00058 0.6 2.4 5.0 10.5 3 7,200 102.2 21.0.00038 5 11.6 19.0 30 E40470 3 1200 38,000 10.0 20.0.0250 b b b b 1 32,500 73.5 21.0.0140 b b b 2 2 26,000 342.0 9.0.00212 b 2 15 132 1 1350 20,000 26.7 27.0.00173 -- 0.4 2.7 6 1 18,500 47.2 26.5.00143 -- 1 4 12.5 3 15,500 142.9 7.5.00097 2 20 34 50 2 13,500 412.4 29.0.00080 15 66 96 125 3 1500 20,000 0.5 54.0.0134 b b b -- 2 15,000 4.3 31.0.00145 -- 0.1 0.2 0.5 2 10,000 43.8 23.5.00075 1 8,000 136.3 -_(d).00050 3 9 18 32 E41286 2 1200 37,000 29.9 8.0.0240 b b b b 1 32,500 68.7 7.0.0180 b b b 1 3 27,000 443.2 4.5.00491 b -- 156 376 2 1350 24,000 18.3 8.0.00190 -- 0.2 0.5 4 1 18,500 100.5 14.0.00097 2.5 16.5 44 61 3 15,000 381. 1 21.0.00075 22 105 180 235 3 1500 15,000 1.8 29.0.00205..... 2 12,500 14.6 28.0.00081 0.2 0.6 1.2 1.9 1 8,000 174.6 18.5.00050 5 17 31.5 52

TABLE X, Continued Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. menea) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in. /in. ) 02 0.5 1.0 2. 0 E41887 3 1200 43,000 17.0 23.5,. 0300 b b b b 1 38,500 51.8 24.0.0270 b b b b 1 38,000 49.8 25.5.0264 b b b b 2 35,000 102.5 22.0.0169 b b b 0.2 3 30,000 320.0 18.0.00482 b -- 12 62 2 1350 23,000 7.8 32.5.00345 b -- -- - 2 21,500 38.4 29.0.00137 -- 0.5 1.5 5.3 1 18,500 84.2 44.0.00110 0.5 2 4.5 20 3 15,000 323.6 18.5.00073 8 31 62 103 3 1500 15,000 6.2 23.0.00148 -- 0.1.4 1.1 2 13,000 18.4 48.5.00112 - - -- 1 8,000 245.7 42.0.00060 -- 2 5 31 E41737 3 1200 37,000 13.3 7.5.029 b b b b 1 32,500 48.6. 6.5.0160 b b b 1.5 2 30,500 79.9 9.0.0127 b b b 18 3 25,000 298.0 6.0.00492 b -- 100 225 3 1350 23,000 21.5 9.0.00184 -- -- - 1 18,500 66.5 8.0.00107 1 6.5 25 47 2 14,000 280.7 15.5.00070 17.5 52 92 127 1 1500 14,000 5.4 24.0.00137 -- 0.15 0.3 0.5 2 12,000 12. 1 11.5.00099 -- 1 9,400 64.9 15.0.00059 0.7 3.7 7 12 1 8,000 124.0 16.0.00054 3 9 16.5 30 7X7935 1 1200 32,500 23.3 11.0.00290 b 0.2 1.0 6.5 3 28,000 75. 1 9.5.00165 0.1 5.5 21 38.5 2 23,500 182.0 7.0.00130 2 45 82 118 1 1350 18,500 29. 1 21.5.00110 0.6 2.6 5.6 10.5 2 15,000 75.7 28.0.00090 1.5 6.5 13 22 3 11,000 180.0 44.0.00060 5 21 39 74 3 1500 12,000 5.1 31.0.00134 -- -- -- 1 8,000 45.1 55.0.00088 0.2 1 2.3 4.7 2 6,200 74.8 38.0.00078 0.4 1.7 4.0 8.7 X25788 2 1200 40,000 18.0 38.5.00305 b -- 1.0 4 1 32,500 47.9 23.0.00174 -- 1.2 4.0 10.3 3 26,000 134.8 24.5. 00148 3 21.5 46 69 2 22,000 291.1 24.5.00116 12 56 85 116 1 1350 18,500 13.0 18.0.00118 0.4 0.7 1.7 3.0 3 13,000 105.9 41.5.00073 1.5 5.4 11 20.5 2 10,500 241.0 44.0.00057 3 10 17 30 2 1500 12,000 4.6 42.0.00151 -- 0.1 0.3 0.6 1 8,000 28.0 62.5.00103 -- 0.5 1.2 2.5 3 6,000 68.8 48.0.00095 -- 1 2.4 6 2 3,900 460.0 24.0.00058 2 6 18 45 3X0005 3 1200 39,000 7.9 >. 04 b b b b 1 32,500 65.8 8.0.0340 b b b b 2 28,000 176.0 4.0.0127 b b b 9 3 25,000 394.6 6.0.00675 b b 2 276 3 1350 23,000 13.3 18.0.00448 b -- 0. 1 1 1 18,500 68.3 24.5.00120 0.6 5 17.5 32 2 14,000 370.1 18.5.00080 27 93 135 169 3 1500 12,000 24. 5 32.0.00107 -- 0.2 0.4 1.2 2 10,000 49.5 21.5.00096 0.4 1.5 3 6 1 8,000 146.7 9.0.00072 2.0 10 27.5 58 (a) Number identifies third of sheet from which specimen was taken. (b) Exceeded indicated deformation on loading. (c) Fractured through gage mark. (d) Fractured outside of gage marks.

TABLE XI STRESS-RUPTURE AND TOTAL DEFORMATION DATA FOR NINE HEATS OF INCONEL X SHEET TESTED AT 1200~, 1350~, AND 1500~F Spec,- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. men/a) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in. /in.) 0. 05 1. 0 Z. 0 Y4474X 1 1200 85,000 1.2 0.5.004 b 2 71,000 16.6 1.5.00296 b 3 63,000 51.3 1.2.00274 b 1 52,500 59.6 0.5.00225 b 1 1350 55,000 10.4 2. 0.00244 b 2 47,000 36.8 1.0.00211 b 3 41,000 92.9 2.0.00184 - 1 34,500 66. 1 0.5.00145 -- 1 1500 32,500 16.5 6.5.00146 3.2 10 2 25,000 75.7 4.5.00117 29.5 54 3 19,000 394 9.0.00085 196 274 317 Y3166X 2 1200 70,000 11.6 1.5.00300 b ~11 - 3 57,000 37.1 1.5(c).00228 b 1 50,000 163.0 1.5.00218 b 2 1350 50,000 5.2 1.0.00242 b - 1 41,000 28.2 1.5(c).00199 - 3 35,000 35.6 1.5.00169 5 - 2 26,000 388.3 0.5.00122 100 2 1500 32,000 9.5 2.5.00160 0.5 5.8 7.5 1 22,000 61.9 3.5.00106 16.5 40 54 3 15,000 295.9 3.5.00069 140 234 282 Y4602X 2 1200 78,000 27.6 2.5.00355 b 3.7 21 -- 1 68,000 72. 3 2.0.00310 b 10 65 3 57,000 350 2.0.00244 b 120 1 1350 55,000 8.0 1.0.00251 b 6 -- -- 3 47,000 44.5 2.5.00230 b 12.5 32 2 39,000 139.3 2.5.00191 0.1 47 104,130 1 33,000 230.5 2.5.00162 2 87 175 2 1500 28,000 21.4 6.0.00153 1 5 10.20 1 21,000 63.5 8.5.00106 2.8 14 26.5 3 14,000 241.2 8.5.00070 20 59 105 160 Y4860X 1 1200 57,000 23.5 1.5.00288 b 2 49,000 60.2 0.5(d).00200 b - 3 43,000 191.2 0.5(d).00172 6 2 1350 42,500 18.2 1.5.00201 b 3 33,000 110. 1 1.0.00145 6.5 -- 2 28,000 326.5 1.0.00132 75 3 1500 28,000 43.8 1.5.00129 6.5 30 1 21,000 126.0 3.5.00095 47 104 120 2 17,000 270.8 2.0.00080 87 184 240 Y4512X 2 1200 62,000 40 2.0.00259 b 1 57,000 98.4 1.5.00218 b 3 50,000 299 1.0.00205 b 3 1350 49,000 14.3 0.5.00210 b 2 38,000 103.2 1.0.00171 6 85 1 33,000 205.8 3.0.00134 15 142 2 1500 27,000 33.0 3.5.00123 3 13.3 24.5 -,30 1 23,000 51.7 3.0.00106 8 25.5 37.0 -50 3 15,000 340. 3 4.0.00067 53 138 212 286

TABLE XI, Continued Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. mena) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in. /in. ) 0. 5 1.0 2.0 Y4511X 1 1200 75,000 10 4 2.0.00308 b 6 -- -- 3 72,000 4.4 0. 5.00296 b 2 63,000 201.5 1.5.00252 b 178 1 57,000 174 2.0.00240 b 91 -- 3 1350 46,000 33.6 2.0.00218 b 17 1 40,000 58.3 2.0.00191 0.5 35.5 -- 2 28,000 720.4 1.5.00130 33 330 546 1 1500 24,000 29.0 5.0.00133 2 7 13 -- 3 18,000 116.5 7.5.00093 14 47 73 105 2 15,000 202.1 5.5.00077 24 75 114 158 Y4847X 2 1200 61,000 38.5 1.5.002 68 b 48 -- -- 1 57,000 51.0 1.5.00240 b -- - 3 49,000 395,9 1.0.00207 b 331 3 1350 45,000 24.8 2.0.00215 b 13 1 35,000 104.8 2.0.00160 3 101 -- 2 30,000 355.4 1.5.00123 56 247 -354 3 1500 28,000 20.8 6.0.00151 0.8 4 7.5 -- 1 21,700 56.6 3.5.00113 6 25 37 48 2 14,000 346.2 8.0.00069 43 125 191 249 Y4984X 2 1200 78,000 22.8 1.5.00315 b ~22 1 68,000 55.1 0.5.00275 b 3 57,000 356.9 1.5.00231 b 232 2 1350 45,000 69.9 0.5.00225 b 41.5 3 38,000 143.2 1.5.00168 1 71.5 138 1 30,000 461.2 2.0.00150 13 260 -420 2 1500 29,000 15 2.0.00163 1 6.5 -14 3 22,500 87.3 3.0.00121 4 25 33 -45 1 18,000 127.0 4.0.00095 15 55 81 110 1 15,500 208.4 2.5.00071 29 91 132 190 253X 1 1200 78,000 27.0 2.0.00344 b 18 -- 2 68,000 19.4 0.5.00300 b 3 57,000 341.7 2.0.00252 b 1 1350 57,000 12.8 0.5.00250 b -10 -- 2 47,000 53.2 1.5.00230 b 25 -52 -- 3 33,000 307.9 1.5.00147 4 196.-300 2 1500 28,000 22.6 1.5.00142 2 12 - 3 22,500 66.3 2.0.00110 10 36 52.5 1 16,000 186.7 3.0.00078 26 86 132 172 (a) Number identifies third of sheet from which specimen was taken. (b) Exceeded indicated deformation on loading. (c) Fractured through gage mark. (d) Fractured outside of gage marks.

TABLE XII STRESS-RUPTURE AND TOTAL DEFORMATION DATA FOR TEN HEATS OF N-155 SHEET TESTED AT 1350~, 1500~, and 1650~F Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. mena) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in./in.) 02 0.5 1.0 2. 0 M624 2 1350 35,000 21.8 15.0.00412 b 0.1 1.2 5.5 3 30,000 56.5 15.5.00201 b 2 4.5 13 1 25,000 182.4 13.0.00135 1 8 22 50 3 23,000 313.8 9.5.00125 2,5 15 40 103 1 1500 22,000 11.5 14.5.00134 -- 0.3 1 2 3 18,000 70.2 21.0.00100 0.2 1.7 6.4 17 2 15,700 165.4 16.0,00087 2 11 32 61 3 14,000 266.0 7.5.00075 5 38 117 192 3 1650 15,500 5.5 21.5.00130 -- 0.25 0.7 1.3 2 13,500 14.9 19.0.00093 0.25 1.3 3 5.5 1 11,500 39.4 12.0.00081 0.8 5.5 12 18.5 3 9,500 124.5 10.0.00069 4.5 26.5 48 72 M206 2 1350 36,000 20.4 16.0.00487 b 3 33,000 46.2 19.0.00251 b 0.8 3.6 11 1 29,000 75.4 16.0.00184 -- 2.3 9.2 21 2 23,000 373.8 9.5.00125 3 16 46.5 122 2 1500 21,500 17.2 20.0.00132 0.1 0.6 1.9 4.2 1 17,500 94.0 16.5.00099 0.3 6.2 18.5 39 3 14,000 366.6 9.5.00070 5 35 179 264 2 1650 16,000 6.0 19.0.00126 0.05 0.4 1.0 2 3 13,000 18.9 17.5.00091 0.7 3.5 6.4 9.7 1 9,800 83.1 15.0.00077 7 22 40 53.5 M208 2 1350 37,000 17.5 11.5.00316 b 0.3 1.1 2.6 2 34,000 42.0 17.0.00248 b 1.0 3.4 10.4 1 29,000 81.1 12.5.00171 0.2 3.2 13.0 29.0 3 24,000 274.9 9.0.00123 3.0 19.0 61.0 115.0 2 1500 21,000 26.3 4.5.00120 0.1 0.9 2.7 5.5 1 17,500 85.5 12.5.00100 0.5 6.5 22 41.5 3 14,200 324.5 9.0.00080 4 63 155 225 2 1650 16,500 5.8 23.0.00110 0.05 0.4 0.9 2.0 3 12,500 26.0 15.5.00070 1.0 5 9.5 12.0 1 10,000 97.4 7.0.00060 9 37 53 74 M207 3 1350 38,000 20.3 20.0.00310 b 0.4 1.6 4.4 2 36,000 32.5 20.5.00278 b 0.4 1.7 5 1 29,000 58.3 9.0.00157 0.3 2.4 7 21.4 3 23,500 526.3 9.0.00126 2 29 91 252 3 1500 21,000 22.0 16.0. 00129. 1 17,500 83.0 19.0.00110 0.5 5.5 13.3 27.5 2 16,500 155.0 15.0.00092 1.5 16.5 52 94 3 14,200 465.0 8.0. 00078 4 54 208 321 2 1650 16,500 5.9 28.0.00129 0.05 0.3 0. 8 1.6 1 13,500 17.1 20.5.00096 0.2 1.1 2.3 4.5 3 10,000 121.5 11.0.00068 8 32 56 79 M733 2 1350 38,000 14.0 22.5.00365 b 0. 2 0.9 2.1 1 28,500 96.5 19.5.00152 0.4 2.4 8.1 22 3 24,000 363.9 18.5.00123 2.5 14 46 125 3 1500 21,500 24.0 34.0.00119 0.1 0.65 1.9 4.5 1 17,500 86.0 23.0. 00096 0.6 6 17.3 32.3 2 14,000 404.4 21.0.00069 11 64 150 233 2 1650 16,500 7.9 42.0.00140 -- 0.1 0.3 0.9 3 12,700 15.0 19.5.00086 0.3 2.1 4.3 7 1 10,200 75.0 12.0.00070 2.7 8.7 19.2 23

TABLE XII, Continued Speci- Temp Stress Rupture Elongation Deformation Time for Indicated Percent Deformation Heat No. mena,) Time on Loading (hours) Location (~F) (psi) (hours) (% in 2 in.) (in. /in.) 0. 0.5 1.0 2. 0 M737 2 1350 35,000 32.3 17.0.00246 b 0.6 2 5.7 3 28,500 87.2 — (d) 00154 0.3 3 10 24 1 23,000 402 7.5(d).00117 3 12 41 145 2 23,000 442 8.5.00111 4 19 50 133 3 1500 21,500 23.0 21.5.00113 0.2 0.9 2.3 5.7 1 17,500 101.0 19.5.00095 0.5 3 10 29 2 14,500 306.0 13.5.00080 3 24 85 157 2 1650 16,500 2.5 8.5(d).00156 -- 0.2 0.4 0.8 3 12,700 28.7 20.0.00093 0.6 2.7 6 11 1 10,200 89.7 23.0.00068 2.5 12.5 26 45 M732 2 1350 37,000 12.0 14.5 00445 b 0. 1 0.7 2.5 1 28,500 84.0 15.0.00152 -- 3 9.2 25 2 23,000 296.0 13.5.00112 3 14 40 91 2 1500 21,000 20.0 27.0.00120 0.1 0.7 1.7 4 1 17,500 68.1 21.5.00100 0.5 4 11.5 22.5 3 14,000 233.0 18.0().00080 5 21 55 96 2 1650 16,000 4.4 32.5.00135 -- 0.1 0.3 0.75 3 12,500 19.0 21.5.00090 0.2 1 2.3 4.7 1 10,200 67. 8 22.0.00076 2 13 19 29.4 M731 3 1350 38,000 15.3 14.0.00315 b 0.4 1.7 3.7 1 28,500 101.2 13.5.00160 0.3 4 15.5 34 2 23,500 559.5 11.0.00120 2 22 106 260 3 1500 22,500 16.0 18.0.00153 -- 0.6 2 3.9 1 17,500 135.7 13.5.00106 1 16 45 73 2 14,500 662.1 8.5.00084 14 82 217 370 1 1650 17,000 4.7 33.0.00175 -- 0.25 0.6 1.1 3 13,500 24.7 20.5.00090 0.5 3.5 7.5 11 2 10,200 162.9 13.0.00062 8 30 54 87 M726 3 1350 38,000 14.0 23.5.00355 b 0.2 2.1 2.7 1 28,500 97.2 17.0.00147 0.4 3.5 10.6 24.2 2 23,500 357.0 14.5.00115 5 23 51 101 1 1500 24,000 12.6 19.0.00150 0.05 0.3 0.75 1.5 3 17,500 78.2 20.0.00095 - 1 15,700 197.6 12.0.00091 2 15 48 93 2 1650 16,500 3.9 30.0.00132 -- 0.15 0.4 0.8 3 13,000 23.5 25.0.00092 0.2 2 3.9 7.3 1 10,200 120.1 18.0.00070 6 26 47 71 M730 3 1350 35,000 28.5 24.5.00295 b 0. 3 1 5 1 28,500 82.5 11.5(c).00148 0.5 2 5.5 19 2 23,000 575. 2 15.5.00105 1 8.5 42 141 1 1500 21,000 10.1 46.0.00117 0.2 0.5 2.3 6 1 17,500 44.0 13.0.00093 1 5.3 14.4 29 2 17,500 87.0 15.5.00089 1.3 6 15.4 30 3 14,500 415.0 18.5.00074 10 51 108 185 2 1650 16,500 8.0 35. 0.00150 -- 0.2 0.5 0.9 3 13,000 24.6 24.5.00085 0.3 2.4 5.3 8.8 1 10,200 87.6 13.0.00063 4.5 18 35 60 (a) Number identifies third of sheet from which specimen was taken. (b) Exceeded indicated deformation on loading. (c) Fractured through gage mark. (d) Fractured outside of gage marks.

TABLE XIII RUPTURE AND TOTAL DEFORMATION STRENGTHS OF TEN HEATS OF TYPE 321 SHEET MATERIAL AT 1200~, 1350~, AND 1500~F Stress for Rupture or Indicated Total Deformation in the Specified Time Period Heat No. 1200~F 1350~F 1500~F 20 Hr 80 Hr 300Hr 5 Hr 20 Hr 80 Hr 300 Hr HrHr 5 Hr 20 Hr 80 Hr RUPTURE STRENGTH, PSI R10356 33,500 28,500 22,500 -- 19,000 15,000 11,500 -- 12,000 10,000 7,100 E02326 34,000 27,500 22,500 -- 17,500 13,500 10,700 -- 13,000 9,600 6,600 E1880 33,500 28,000 23,500 -- 21,500 16,500 13,000 -- 14,800 11,200 8,500 X25677 33,500 29,500 23,500 -- 20,500 16,000 12,500 -- 13,200 11,500 6,700 E41024 33,500 31,000 24,500 -- 22,000 18,500 14,600 -- 13,600 11,000 8,800 627967 32,000 27,500 22,500 -- 19,000 16,000 13,000 -- 14,000 10,800 8,200 R30409 34,500 27,500 22,000 -- 20,500 15,500 11,300 -- 12,000 10,300 7,500 E1869 36,000 29,500 24,000 -- 21,000 17,500 13,500 -- 15,500 12,500 7,800 X46099 31,000 26,000 21,000 -- 18,000 14,300 11,500 -- 13,500 9,900 7,200 X13043 29,500 25,000 19,500 -- 17,500 14,000 10,500 -- 12,500 9,500 7,200 2,0% DEFORMATION STRENGTH, PSI R10356 29,500 24,000 19,000 -- 16,000 12,500 9,700 12,200 10,000 7,400 5,400 E02326 28,000 24,500 20,000 -- 16,300 11,700 8,600 14,500 10,000 7,400 5,700 E1880 25,000 23,500 22,000 21,500 17,500 14,200 11,000 15,200 11,700 8,800 6,700 X25677 28,500 25,000 21,000 20,500 17,000 12,800 9,600 12,200 9,800 7,600 -- E41024 26,500 25,500 21,000 21,500 20,000 17,000 14,000 13,500 12,000 9,800 7,900 627967 29,000 24,000 20,000 -- 17,500 14,500 12,000 14,000 11,300 9,300 7,800 R30409 27,500 24,000 19,500 -- 16,500 13,000 10,200 11,500 10,200 8,300 (4,600) E1869 29,500 27,000 22,000 -- 18,500 15,500 (12,000) -- 12,500 10,500 (6,600) X46099 25,000 21,000 18,000 17,500 14,000 11,500 (9,600) 12,000 9,000 7,100 -- X13043 23,500 19,500 16,000 -- 14,500 10,000 -- -- 9,200 6,800 1.0% DEFORMATION STRENGTH, PSI R10356 24,000 22,500 -- 18,000 14,000 11,000000,00 11,500 8,800 6,200 E02326 25,500 23,000 -- -- 14,500 10,500 (7,600) 12,500 8,800 6,400 -- E1880 24,000 22,500 -- 19,000 16,500 12,500 (9,300) 14,000 10,300 7,800 5,800 X25677 25,500 23,000 -- 18,500 15,500 12,000 (9,000) 11,300 9,000 6,700 -- E41024 -- -- -- 19,500 18,500 16,000 13,000 12,500 11,200 9,000 7,200 627967 26,500 22,500 -- - 15,500 13,500 (11,500) 12,500 10,100 8,400 7,000 R30409 24,500 21,500 -- 17,000 15,000 11,500 (9,000) 11,000 9,800 6,800 -- E1869 26,000 24,000 -- -- 17,000 14,000 -- 14,200 11,700 9,000 -- X46099 23,000 20,000 -- 15,500 12,500 10,000 -- 10,400 8,000 6,400 X13043 22,000 17,500 -- 16,500 12,000 -- - 11,000 7,600 5,600 0. 5% DEFORMATION STRENGTH, PSI R10356 23,000 -- -- 16,000 12,000 9,500 -- 10,500 7,400 (5,600) E02326 22,500 20,500 -- -- 13,000 8,700 -- 11,000 7,400 (5,300) E1880 22,500 21,000 -- 17,500 14,500 (9,600) -- 12,300 8,800 6,600 X25677 23,000 (20,000) -- 17,000 14,500 (9,800) -- 9,800 7,700 -- E41024 -- -- -- 18,000 17,000 14,000 -- 12,000 10,300 8,100 627967 25,000 21,000 -- 16,000 14,300 12,500 -- 11,500 9,100 7,500 R30409 - -- - 16,000 14,000 (9,600) -- 10,500 9,300 (5,400) E1869 -- -- -- 19,500 15,500 12,500 -- 12,800 10,500 (7,200) X46099 21,500 -- -- 13,500 11,000 -- -- 8,700 7,000 (5,700) X13043 19,000 -- -- 14,000 9,200 -- -- 9,500 6,300 -- 0. 2% DEFORMATION STRENGTH, PSI R10356 - -- -- 12,500 10,000 -- — 8,300 6,000 E02326 -- -- -- 13,500 10,500 -- -- 8,200 5,500 E1880 -- -- -- 14.,000 10,500 -- -- 10,500 6,600 - X25677 -- -- -- 15,000 12,000 -- — 8,700 6,200 E41024 -- -- -- 17,000 16,000 -.- 10,500 8,200 627967 23,000 -- -- 14,500 12,800 - — 9,000 7,200 R30409 -- - - 15,000 11,000 -- — 9,800 6,300 E1869 -- -- -- 15,500 12,500 -- -- 11,000 8,600 -- X46099 -- -- -- 10,300 -- - -- 7,500 6,000 -- X13043 -- -- - 9,600 -- -- -- 7,200 -- -- Note: Parentheses around strength values indicate extrapolated values.

TABLE XIV RUPTURE AND TOTAL DEFORMATION STRENGTHS OF TEN HEATS OF TYPE 347 SHEET MATERIAL AT 1200~, 1350~, AND 1500~F Stress for Rupture orIndicated Total Deformation in the Specified Time Period Heat No. 1200~F 1350~F 1500~F 20 Hr 80 Hr 300 Hr 5r 20 Hr 80 0 H300 H r Hr Hr 5 Hr 20 Hr 80 Hr RUPTURE STRENGTH, PSI 620809 38,000 32,500 28,000 - 23,000 18,000 14,000 -- 13,500 11,500 8,300 620813 38,500 33,500 29,000 -- 23,500 19,000 15,000 -- 15,000 11,500 8,300 636862 38,000 32,000 28,000 -- 24,000 18,000 13,500 -- 13,000 10,500 7,700 E40470 36,000 32,000 26,500 -- 20,000 17,000 14,000 -- 14,200 10,500 9, 000 E41286 37,500 32,000 28,000 -- 23,500 19,000 15,500 -- 13,500 11,800 9,200 E41887 42,000 36,000 30,000 -- 22,000 18,500 15,000 - 15,000 12,800 9,800 E41737 36,000 30,000 25,000 -- 23,000 18,000 14,000 -- 14,000 11,000 8,800 7X7935 33,000 28,000 21,500 - 20,000 14,500 9,000 -- 12,000 9,200 6,000 X25788 39,000 29,000 22,000 -- 17,000 13,500 10,000 -- 12,000 8,400 6,000 3X0005 36,000 31,000 26,000 -- 22,000 18,000 14,500 -- (14,000) 12,000 9,000 2. 0% DEFORMATION STRENGTH, PSI 620809 31,000 27,500 -- 20,500 19,000 16,000 (12,000) 13,000 11,000 8,400 -- 620813 30,000 29,000 27,000 21,500 20,000 16,500 (13,300) 12,000 9,800 8,200 636862 29,000 26,500 -- 21,500 19,500 14, 500 (11,000) 13,000 10, 600 8,100 E40470 29,500 27,500 -- 20,500 17,500 14,500 (12,000) 13,500 10,500 8,500 E41286 30,500 29,000 27,000 23,500 21,500 17,500 14 500 13,500 11,000 9,000 7,600 E41887 -- 29,000 -- 21500 18,500 18 500 (1315 500 (11000 8,600 E41737 30.000 28,000 24.000 -- 21,500 16, 000 (12, 500) 12,700 10,400 8,600 7X7935 30,500 25,000 (20,000) -- 15,500 10,600 - -- 7,800 -- X25788 30,000 24,000 -- 17,000 12,500 -- -- 10,000 6,600 4,800 3X0005 27,000 26,000 24,500 21,000 19,000 16,000 13,000 13,000 10,800 9,000 7,700 1.0% DEFORMATION STRENGTH, PSI 620809 -- -- -- 20,000 18,000 14,000 -- 12,000 10,000 7,600 -- 620813 -- -- -- 19,000 18, 000 15,300 -- 11,000 9, 000 7,500 636862 -- -- - 19,000 17, 000 13,500 -- 12,000 9, 600 7,100 E40470 26,000 -- -- 19,000 16,500 13,800 -- 12,000 9,600 7,800 E41286 -- -- -- 21,000 19,500 16,800 -- 12,800 10,200 8,400 E41887 29,500 -- -- 19,000 17,000 14,500 -- 11,000 8,000 - E41737 -- 25,500 - -- 19,000 14,500 -- 11,700 9,700 7,800 7X7935 28,000 23,000 -- 19,500 13,000 9,000 -- -- 5,600 - X25788 28,000 22, 00 -- 14,000 10, 500 -- -- 7,800 5, 300 -- 3X0005 - -- -- 20,000 18,000 15,000 -- 11,600 9,800 8,400 0. 5% DEFORMATION STRENGTH, PSI 620809 - -- -- 19,000 15,500 - - 11,000 9,000 -- 620813 -- -- -- 17,500 16,000 - -- -- 8,400 636862 -- -- -17,500 16,000 - -- 10,500 8,700 E40470 - -- -- 16,500 15,000 13,000 -- 11,000 8,600 -- E41286 - -- -- 19,000 18,000 15,500 -- 11,500 9,400 7,800 E41887 - -- -- 17,500 15,500 -- - 9,200 -- -- E41737 -- - -- 19,000 16,500 13,000 -- 10,800 9,000 - 7X7935 26,000 21,000 -- 16,000 11,000 - - 8,000 -- - X25788 26,000 21,000 -- 12,000 9,000 -- - 6,200 4,100 -- 3X0005 -- -- -- 18, 000 17,000 14,000 -- 10,200 8,600 7,400 0.2% DEFORMATION STRENGTH, PSI 620809 -- -- -15,500 -- -- -- 9,000 7,500 -- 620813 -- -- - 16,000 -- - - 7,400 636862 -- -- -- 14,500 - - -- 9,000 7,200 E40470 -- -- - 14,500 -- -- -- 9,400 7,400 E41286 -- -- -17,500 15,000 -- - 9,800 8,000 E41887 -- -- -- 15,500 - -- - E41737 -- -- -- 16,000 14,000 - -- 9,000 7,500 -- 7X7935 -- - - 11,000 -- -- -- __ _ X25788 20,500 -- -- 9,400 -- -- -- 4,600.. __ 3X0005 -- -- -- 16,000 14,500 -- -- 8,500 7,200 -- Note: Parentheses around strength values indicate extrapolated values.

TABLE XV RUPTURE AND TOTAL DEFORMATION STRENGTHS OF NINE HEATS OF INCONEL X SHEET MATERIAL AT 1200~, 1350~, AND 1500~F Stress For Rupture or Indicated Total Deformation in the Specified Time Period Heat No. 1200~F 1350~F 1500~F 20 Hr 80 Hr 300 Hr 20 Hr 80 Hr 300 Hr Z0 Hr 80 Hr 300 Hr RUPTURE STRENGTH, PSI Y4474X 68,000 55,000 45,500 49,000 38,500 30,000 31,500 25,000 20,000 Y3166X 64,000 53,000 44,000 41,000 33,000 27,000 27,000 20,000 15,000 Y4602X 80,000 68,000 58,000 50,000 42,000 32,000 28,500 19,300 13,000 Y4860X 57,000 47,500 40,000 42,500 34,500 28,000 32,000 23,500 16,500 Y4512X 68,000 58,500 50,000 47,000 38,000 32,000 29,500 21,200 15,500 Y4511X 69,000 64,000 60,000 48,500 39,500 32,500 26,000 19,000 14,000 Y4847X 66,000 57,500 50,000 45,000 37,000 30,500 27,500 20,000 14,500 Y4984X 78,000 67,000 58,000 54,000 42,500 33,000 27,500 20,000 15,000 253X 74,000 65,000 57,000 54,000 42,500 33,000 29,000 21,000 15,000 2. 0% DEFORMATION STRENGTH, PSI Y4474X --. Y3166X Y4602X -- - -- -- -- 27,500 17,500 11,500 Y4860X -- -- - Y4512X -- -- -- -- -- 29,000 20,500 14,800 Y4511X - -- -- -- -- -- -- 18,000 13,600 Y4847X -- -- -- - -- -- 25,500 19,000 13,500 Y4984X -- -- -- -- -- -- 27,000 19,500 14,000 253X -- - -- - -- --- 20,000 (14,200) 1. 0% DEFORMATION STRENGTH, PSI Y4474X -- -- -- -- -- -- -- -- 19,500 Y3166X -- -- -- -- -- -- 26,000 19,500 14,700 Y4602X 78,000 66,000 -- 48,500 39,000 29,000 22,500 15,000 (10,300) Y4860X -- -- - - -- 23,000 16,000 Y4512X - -- -- -- -- -- 27,500 19,200 13,800 Y4511X - -- -- -- -- -- 22,000 17,000 13,000 Y4847X -- -- -- -- -- -- 23,500 17,500 12,500 Y4984X -- -- -- -- -- 32,000 26,000 18,000 12,500 253X -- -- -- -- -- -- -- 19,000 (13,500) 0.5% DEFORMATION STRENGTH, PSI Y4474X -- -- -- -- -- -- 29,500 23,500 19,000 Y3166X -- -- -- -- -- -- 25,000 19,000 14,200 Y4602X 66,000 59,000 -- 44,000 34,000 -- 19,000 13,000 Y4860X -- -- -- -- -- -- 29,000 21,000 15,000 Y4512X - -- -- -- -- -- 4,500 17,000 12,500 Y4511X -- -- -- 44,500 35,000 28,500 20,000 15,500 Y4847X 64,000 56,000 49,000 42,500 35,000 29,000 22,000 15,500 11,000 Y4984X -- -- -- 49,000 38,000 28,500 23,500 16,000 11,000 253X -- -- -- 49,000 38,500 30,500 24,500 17,000 0. 2% DEFORMATION STRENGTH, PSI Y4474X -- -- -- -- -- -- 26,000 21,500 18,000 Y3166X -- - -- 31,500 27,000 -- 21,000 16,500 13,200 Y4602X -- -- -- -- -- -- 14,000 -- -- Y4860X -- -- -- 30,500 27,500 -- 24,000 17,500 Y4512X -- -- -- -- -- -- 18,500 14,000 Y4511X -- -- -- -- -- -- 16,500 -- Y4847X -- -- -- 31,500 29,500 -- 16,500 12,000 Y4984X -- -- -- 29,000 -- -- 17,000 12,500 253X -- -- -- -- -- -- 18,000 (11,500) -- Note: Parentheses around strength values indicate extrapolated values,

TABLE XVI RUPTURE AND TOTAL DEFORMATION STRENGTHS OF TEN HEATS OF N155 SHEET MATERIAL AT 1350~, 1500~, AND 1650~F Stress for Rupture or Indicated Total Deformation in the Specified Time Period Heat 1350~F 1500~F 1650~F No. 5 Hr 20 Hr 80 Hr 300 Hr 5 Hr 20 Hr 80 Hr 300 Hr 1 Hr 5 Hr 20 Hr 80 Hr RUPTURE STRENGTH, PSI M624 -- 35,000 28,500 23,000 -- 20,500 18,500 14,000 - 16,000 13,000 10,200 M206 -- 37,000 29,500 24,000 - 21,000 18,000 14,500 -- 16,500 12,800 9,800 M208 -- 37,500 29,500 23, 500 -- 22,000 17,500 14,500 -- 16,500 13,000 10,300 M207 -- 37,000 31,000 25,500 - 21,000 18,000 15,000 -- 17,000 13,500 10,500 M733 -- 36,000 29,500 24,000 - 22,000 18,000 14,500 -- 17,500 13,500 10,100 M737 -- 37,000 30,000 24,500 -- 22,000 18,000 14,500 -- 16,000 13,000 10,300 M732 - 35,000 28,000 23,000 -- 21,000 17,000 13,500 - 16,000 12,500 10,000 M731 - 36,000 30,000 25,000 -- 22,000 18,500 16,000 -- 17,000 14,000 11,500 M726 -- 36,000 29,000 24,000 -- 21,500 18,000 14,800 -- 16,000 13,200 11,000 M730 -- 34,500 28,500 24,000 -- 19,500 17,000 15,000 -- 17,000 13,300 10,400 2.0% DEFORMATION STRENGTH, PSI M624 35,000 29,000 24,000 (19,500) 20,000 17,500 15,500 (13,500) 16,000 13,500 11,300 9,300 M206 36,000 29,500 24,500 (20,000) 21,500 18,500 16,000 (14,000) 17,500 14,000 11,500 9,200 M208 35,000 30,500 25,000 (21,000) 21,000 18,500 16,200 (14,000) 17,500 14,500 12,000 10,000 M207 35,500 30,500 26,500 23,000 19,500 18,000 16,500 14,500 17,000 14,000 12,000 10,000 M733 34,000 30,500 25,000 (22,000) 21,500 18,500 16,000 13,800 16,5 00 13,200 11,000 9,100 M737 35,500 29,500 25,000 (21,000) 22,000 18,500 15,500 13,500 16,500 14,000 11,500 9,400 M732 34,000 29,000 24,000 (20,500) 20,500 18,000 14,500 (12,000) 15,000 12,500 10,700 9,200 M731 36,500 31,000 27,000 23,000 22,000 19,500 17,200 15,000 17,000 15,000 12,500 10,300 M726 35,000 29,000 24,000 (20,000) 22,000 19,000 16,000 13,800 16,000 13,500 11,700 10,100 M730 34,000 29,000 24,500 (21,000) 21,500 18,500 16,000 (14,000) 16,300 14,000 11,800 9,800 1.0% DEFORMATION STRENGTH, PSI M624 29,500 25,000 21,500 (18,000) 18,500 16,500 14,500 (13,000) 15,000 12,500 10,500 8,800 M206 31,500 26,000 21,000 (17,500) 20,000 17,500 15,000 (13,500) 16,000 13,300 11,000 8,800 M208 32,500 27,500 23,000 (19,500) 20,000 17,500 15,000 (13,000) 16,500 13,500 11,500 9,500 M207 31,000 27,500 24,000 (21,000) 18,500 17,000 15,500 13,500 15,500 13,000 11,000 9,600 M733 31,000 27,500 23,000 (20,000) 19,500 17,000 15,000 13,000 15,500 12,500 10,000 8,400 M737 31,500 26,000 21,500 (18,500) 19,500 16,800 14,500 (12,800) 15,000 13,000 10,500 8,800 M732 30,000 25,000 21,500 (18,500) 19,000 15,000 13,000 (11,000) 13,500 12,000 10,200 8,800 M731 33,000 28,000 24,000 (21,000) 21,000 18,500 16,200 14,000 16,000 14,000 11,500 9,800 M726 32,500 27,000 22,000 (18,500) 20,000 17,500 15,000 (12,500) 15,000 12,700 11,000 9,700 M730 29,000 25,000 21,500 (18,500) 19,500 17,000 15,000 (13,000) 15,500 13,000 11,000 9,200 0.5% DEFORMATION STRENGTH, PSI M624 26,500 22,000 -- -- 16,500 14,500 -- -- 13,500 11,500 9,80C -- M206 26,000 22,000 -- -- 18,000 15,000 - -- 15,000 12,200 10,000 M208 28,000 24,000 -- -- 18,500 16,000 -- -- 15,000 12,500 10,500 M207 27,500 24,000 -- -- 17,500 16,000 -- - 14,000 12,000 10,500 M733 26,500 24,000 -- - 17,500 15,500 -- - 14,000 11,000 9,100 M737 26,500 22,500 - -- 17,000 14,500 -- - 14,000 12,000 9,700 M732 26,500 22,000 -- - 17,000 14,000 -- -- 12,500 11,000 9,800 M731 27,500 24,000 -- -- 19,000 17,000 - -- 14,500 13,000 10,800 M726 27,000 23,500 -- -- 17,500 15,000 -- -- 14,000 12,000 10,300 M730 25,500 21,000 -- - 17,500 16,000 -- -- 14,500 12,000 10,000 0.2% DEFORMATION STRENGTH, PSI M624 22,000 -- -- -- 14,000 -- -- -- 10,000 9,400 -- M206 21,500 -- -- -- 15,000 -- -- -- 12,500 10,200 M208 22,500 -- -- -- 14,000 -- -- -- 12,500 10,500 M207 21,500 -- -- -- 14,500 -- - -- 12,000 10,500 M733 22,000 -- -- -- 15,000 -- - -- 12,000 9,400 M737 22,000 -- -- -- 14,000 -- -- -- 11,500 9,400 M732 21,500 -- -- -- 14,000 -- -- -- 10,500 9,400 -- -- M731 21,000 -- -- -- 15,500 -- -- -- 12,500 10,800 -- -- M726 23,500 -- -- -- 15,000 -- -- -- 12,000 10,300 -- -- M730 21,000 -- -- -- 15,000 -- -- -- 12,000 10,000 -- -- Note: Parentheses around strength values indicate extrapolated values.

TABLE XVII ROOM TEMPERATURE TENSILE DATA FROM TYPE 321, TYPE 347, INCONEL X AND N155 SHEET MATERIAL Material Properties Type 321(1) Type 347(2) Inconel X(2) N155(1) TENSILE STRENGTH, PSI Range 81,500/ 87,500/ 156,500/ 116,600/ 92,800 102,000 185,800 121,200 Maximum differ- 4,000 3,000 3,500 2,300 ence for one heat Average 85,550 94,400 174,000 119,050 Standard deviation 3,380 3,840 7,900 1,320 0. 1% OFFSET YIELD STRENGTH, PSI Range 27,500/ 32,500/ 99,500/ 47,900/ 43,500 51,000 132,500 58,000 Maximum differ- 4,500 10,000 5,500 6,200 ence for one heat Average 32,900 39,800 118,000 52,250 Standard deviation 3,960 4,490 8,550 2,340 0.2% OFFSET YIELD STRENGTH, PSI Range 30,000/ 35,500/ 102,000/ 55,400/ 45,500 54,000 136,000 64,500 Maximum differ- 3,500 8,500 6,000 5,000 ence for one heat Average 36,000 43,300 121,500 59,550 Standard deviation 3,910 4,540 8,725 2,230 PROPORTIONAL LIMIT, PSI Range 14,000/ 14,000/ 76,500/ 17,000/ 22,000 28,000 110,000 29,000 Maximum differ- 7,500 9,000 7,000 9,000 ence for one heat Average 16,300 19,800 91,100 21,575 Standard deviation 2,440 3,850 8,890 3,850 ELONGATION, % IN 2 INCHES Range 51.0/ 51.5/ 23.5/ 51.5/ 74.7 64.5 32.0 57.5 Maximum differ- 5.4 5, 5 5.0 3.0 ence for one heat Average 64.4 59. 1 28.0 53. 8 Standard deviation 5.65 4.74 2. 86 1.47 (1) Based on values from 10 heats. (2) Based on values from 9 heats.

TABLE XVIII STATISTICAL EVALUATION OF STRESS RUPTURE AND TOTAL DEFORMATION STRENGTHS OF TEN HEATS OF TYPE 321 SHEET AT 1200~, 1350~, AND 1500~F Rupture or Temp Number Range in Rupture Average Standard Average i Total Deformation of or Deformation Strength Deviation 3 Times Standard Time (hours) (~F) Heats* Strength (psi) (psi) (psi) Deviation (psi) RUPTURE STRENGTHS 20 1200 10 29,500/36,000 33,100 1740 27,900/38,300 80 10 25,000/31,000 28,000 1660 23,000/33,000 300 10 19,500/24,500 22,550 1405 18,300/26,800 20 1350 10 17,500/22,000 19,650 1580 14,900/24,400 80 10 13,500/18,500 15,700 1490 11,200/20,200 300 10 10,500/14,600 12,200 1250 8,400/15,900 5 1500 10 12,000/15,500 13,400 1080 10,200/16,600 20 10 9,500/12,500 10,650 900 7,900/13,300 80 10 6,600/ 8,800 7,550 710 5,400/ 9,700 2.0% TOTAL DEFORMATION STRENGTHS 20 1200 10 23,500/29,500 27,200 1930 21,400/33,000 80 10 19,500/27,000 23,800 2010 17,800/29,800 300 10 16,000/22,000 19,850 1750 14,600/25,100 20 1350 10 14,000/20,000 16,800 1680 11,800/21,800 80 10 10,000/17,000 13,250 2020 7,200/19,300 300 9 8,600/14,000 10,750 1580 6,000/15,500 1 1500 8 11,500/15,200 13,150 1260 9,400/16,900 5 10 9,000/12,500 10,550 1160 7,100/14,000 20 10 6,800/10,500 8,300 1080 5,100/11,500 80 7 4,600/ 7,900 6,400 1140 3,000/ 9,800 1.0% TOTAL DEFORMATION STRENGTHS 20 1200 9 22,000/26,500 24,550 1380 20,400/28,700 80 9 17,500/24,000 21,850 1915 16,100/27,600 5 1350 7 15,500/19,500 17,700 1330 13,700/21,700 20 10 12,000/18,500 15,100 1880 9,500/20,740 80 9 10,000/16,000 12,350 1790 7,000/17,700 300 7 7,600/13,000 9,750 1670 4,700/14,800 1 1500 10 10,400/14,200 12,100 1180 8,600/15,600 5 10 7,600/11,700 9,550 1260 5,800/13,300 20 10 5,600/ 9,000 7,250 1160 3,800/10,800 0.5% TOTAL DEFORMATION STRENGTHS 20 1200 7 19,000/25,000 22,350 1680 17,300/27,400 5 1350 9 13,500/19,500 16,400 1590 11,600/21,200 20 10 9,200/17,000 13,500 2130 7,100/19,900 80 8 8,700/14,000 10,750 1800 5,300/16,100 1 1500 10 8,700/12,800 10,850 1310 6,900/14,800 5 10 6,300/10,500 8,400 1400 4,200/12,600 20 8 5,300/ 8,100 6,450 950 3,600/ 9,300 0. 2% TOTAL DEFORMATION STRENGTHS 5 1350 10 9,600/17,000 13,700 2180 7,200/20,200 20 8 10,000/16,000 11,900 1910 6,200/17,600 1 1500 10 7,200/11,000 9,050 1255 5,300/12,800 5 9 5,500/ 8,600 6,750 1000 3,700/ 9,700 * Number of heats for which data were available for indicated strength value.

TABLE XIX STATISTICAL EVALUATION OF STRESS RUPTURE AND TOTAL DEFORMATION STRENGTHS FOR TEN HEATS OF TYPE 347 SHEET AT 1200~, 1350', AND 1500~F Rupture or Temp Number Range in Rupture Average Standard Average i Total Deformation of or Deformation Strength Deviation 3 Times Standard Time (hours) (~F) Heats* Strength (psi) (psi) (psi) Deviation (psi) RUPTURE STRENGTHS 20 1200 10 33,000/42,000 37,400 2250 30,600/44,100 80 10 28,000/36,000 31,600 2160 25,100/38,100 300 10 21,500/30,000 26,400 2700 18,300/34,500 20 1350 10 17,000/24,000 21,800 2080 15,600/28,000 80 10 13,500/19,000 17,350 1770 12,000/22,700 300 10 9,000/15,500 13,450 2070 7,200/19,700 5 1500 10 12,000/15,000 13,620 1005 10,600/16,600 20 10 8,400/12,800 10,920 1250 7,200/14,700 80 10 6,000/ 9,800 8,210 1230 4,500/11,900 2.0% TOTAL DEFORMATION STRENGTHS 20 1200 9 27,000/31,000 29,700 1110 26,400/33,000 80 10 24,000/29,000 27,150 1660 22,200/32,100 5 1350 8 17,000/23,500 20,900 1710 15,800/26,000 20 10 12,500/21,500 18,450 2620 10,600/26,300 80 9 10,600/17,500 15,250 1850 9,700/20,800 300 8 11,000/14,500 12,700 980 9,800/15,600 1 1500 9 10,000/15,000 12,900 1265 9,100/16,700 5 10 6,600/11,000 9,950 1420 5,700/14,200 20 9 4,800/ 9,000 8,150 1185 4,600/11,700 1. 0% TOTAL DEFORMATION STRENGTHS 5 1350 9 14,000/21,500 19,200 2030 13,100/25,300 20 10 10,500/19,500 16,650 2650 8,700/24,600 80 9 9,000/16,800 14,100 1880 8,500/19,700 1 1500 9 7,800/12,800 11,300 1350 7,200/15,300 5 10 5,300/10,200 8,680 1720 3,500/13,800 20 7 7,100/ 8,400 7,800 437 6,500/ 9,100 0.5% TOTAL DEFORMATION STRENGTHS 5 1350 10 12,000/19,000 17,200 1990 11,200/23,200 20 10 9,000/18,000 14,950 2540 7,300/22,600 1 1500 9 6,200/11,500 9,800 1635 4,900/14,700 5 8 4,100/ 9,400 8,220 1590 3,400/13,000 0.2% TOTAL DEFORMATION STRENGTHS 5 1350 10 9,400/17,500 14,590 2365 7,500/21,700 1 1500 7 4,600/ 9,800 8,470 1625 3,600/13,300 5 7 7,200/ 8,000 7,450 154 7,000/ 7,900 * Number of heats for which data were available for indicated strength value.

TABLE XX STATISTICAL EVALUATION OF STRESS RUPTURE AND TOTAL DEFORMATION STRENGTHS FOR NINE HEATS OF INCONEL X SHEET AT 1200~, 1350~, AND 1500~F Rupture or Temp Number Range in Rupture Average Standard Average i Total Deformation of or Deformation Strength Deviation 3 Times Standard Time (hours) (~F) Heats* Strength (psi) (psi) (psi) Deviation (psi) RUPTURE STRENGTHS 20 1200 9 57,100/80,000 69,300 6700 49,200/89,400 80 9 47,500/68,000 59,500 6580 39,800/79,200 300 9 40,000/60,000 51,400 6800 31,000/71,800 20 1350 9 41,000/54,000 47,900 4250 35,200/60,600 80 9 33,000/42,500 38,600 3230 28,900/48,300 300 9 27,000/33,000 30,900 2060 24,700/34,100 20 1500 9 26,000/32,000 28,700 1900 23,000/34,400 80 9 19,000/25,000 21,000 1890 15,300/26,700 300 9 13,000/20,000 15,400 1870 9,800/21,000 2. 0% TOTAL DEFORMATION STRENGTHS 80 1500 6 17,500/20,500 19,100 1060 15,900/22,300 300 5 11,500/14,800 13,600 1030 10.500/16,700 1.0% TOTAL DEFORMATION STRENGTHS 20 1500 6 22,000/27,500 24,600 1950 18,800/30,400 80 8 15,000/23,000 18,500 2180 12,000/25,000 300 9 10,300/19,500 14,000 2450 6,700/21,300 0. 5% TOTAL DEFORMATION STRENGTHS 20 1500 9 19,000/29,500 24,100 3470 13,700/34,500 80 9 15,000/23,500 17,700 2730 9,500/25,900 300 6 11,000/19,000 13,800 2770 5,500/22,100 0. 2% TOTAL DEFORMATION STRENGTHS 20 1500 9 14,000/26,000 19,100 3660 8,100/30,100 80 7 11,500/21,500 15,100 3370 5,000/25,200 * Number of heats for which data were available for indicated strength value.

TABLE XXI STATISTICAL EVALUATION OF STRESS RUPTURE AND TOTAL DEFORMATION STRENGTHS FOR TEN HEATS OF N155 SHEET AT 1350~, 1500~, AND 1650~F Rupture or Temp Number Range in Rupture Average Standard Average i Total Deformation of or Deformation Strength Deviation 3 Times Standard Time (hours) (~F) Heats* Strength (psi) (psi) (psi) Deviation (psi) RUPTURE STRENGTH 20 1350 10 34,500/37,500 36,100 970 33,200/39,000 80 10 28,000/31,000 29,350 840 26,800/31,900 300 10 23,000/25,500 24,050 757 21,800/26,300 20 1500 10 19,500/22,000 21,250 783 18,900/23,600 80 10 17,000/18,500 17,850 503 16,300/19,400 300 10 13,500/16,000 14,630 627 12,700/16,500 5 1650 10 16,000/17,500 16,550 522 15,000/18,100 20 10 12,500/14,000 13,180 399 12,000/14,400 80 10 9,800/11,500 10,410 476 9,000 /11,800 2.0% TOTAL DEFORMATION STRENGTHS 5 1350 10 34,000/36,500 35,050 819 32,600/37,500 20 10 29,000/31,000 29,750 750 27,500/32,000 80 10 24,000/27,000 24,950 986 22,000/27,900 300 10 19,500/23,000 21,100 1156 17,600/24,600 5 1500 10 19,500/22,000 21,150 840 18,600/23,700 20 10 17,500/19,500 18,450 522 16,900/20,000 80 10 14,500/17,200 15,940 664 13,900/17,900 300 10 12,000/15,000 13,810 739 11,600/16,000 1 1650 10 15,000/17,500 16,530 727 14,300/18,700 5 10 12,500/15,000 13,820 657 11,800/15,800 20 10 10,700/12,500 11,600 496 10,100/13,100 80 10 9,100/10,300 9,640 420 8,400/10,900 1. 0/o TOTAL DEFORMATION STRENGTHS 5 1350 10 29,000/33,000 31,150 1266 27,400/35,000 20 10 25,000/28,000 26,450 1127 23,100/29,800 80 10 21,000/24,000 22,300 1052 19,100/25,500 300 10 17,500/21,000 19,100 1158 15,600/22,600 5 1500 10 18,500/21,000 19,550 723 17,400/21,700 20 10 15,000/18,500 17,030 853 14,500/19,600 80 10 13,000/16,200 14,870 782 12,500/17,200 300 10 11,000/14,000 12,930 758 10,700/15,200 1 1650 10 13,500/16,500 15,350 777 13,000/17,700 5 10 12,000/14,000 12,950 538 11,300/14,600 20 10 10,200/11,500 10,820 482 9,400/12,300 80 10 8,400/ 9,800 9,140 458 7,800/10,500 0. 5% TOTAL DEFORMATION STRENGTHS 5 1350 10 25,500/28,000 26,700 813 24,300/29,100 20 10 21,000/24,000 22,900 1068 19,700/26,100 5 1500 10 16,500/19,000 17,600 700 15,500/19,700 20 10 14,000/17,000 15,350 839 12,000/18,000 1 1650 10 12,500/15,000 14,100 700 12,000/16,200 5 10 11,000/13,000 11,920 589 10,200/13,700 20 10 9,100/10,800 10,050 467 8,600/11,500 0.2%/ TOTAL DEFORMATION STRENGTHS 5 1350 10 21,000/23,500 21,850 709 19,700/24,000 5 1500 10 14,000/15,500 14,600 538 13,000/16,200 1 1650 10 10,000/12,500 11,750 813 9,300 /14,200 5 10 9, 100/10,800 9,900 521 8,400/11,600 * Number of heats for which data were available for i'.ic,.:at.,' strengtlh value.

___I- zz" --— I.22" 1-1/4"' - RTR. T.T.T. L.T. THIS - M.T. 1" -| H.T. First SECTION ~ Section All specimens stamped SHEARED to identify location OFF H.T. M.T. L. T. R. T. T. T.= Second eM Section... —. _ L.T, Direction M, T, of Rolling _H T-h Third iV~~~~fl~ [f |X Reduced SectSectionction 2-1/4" long 1/2" wide 4 —------------------- 36" > Code: L.T. = Lowest Temperature M.T. = Middle Temperature H.T. = Highest Temperature R. T. T. T. = Room Temperature Tensile Test Figure 1. - Sketch Indicating Sampling Procedure of Sheet Materials Submitted with 27-Inch Dimension Parallel to Rolling Direction.

1-1/4"1 R. T T.T. ^_____ - -__________________ L. T. _ I_ ^___________________M.T. First Section I1l H. T. All specimens stamped to identify location H.T. ~______________________ M. T. L. T. R. T. T. T. Secon Section Direction of Rolling L.T. -=M. T. Third H.T. Section Reduced Section 2-1/4" long 1/2" wide 4<- ------------ 24" - or 27" Code: L. T. = Lowest Temperature M. T. = Middle Temperature H. T. = Highest Temperature R. T. T. T. = Room Temperature Tensile Test Figure 2. - Sketch Indicating Sampling Procedure of Sheet Materials Submitted with the 36-Inch Dimension Parallel to Direction of Rolling.

Hole for Attaching Optical Extensometer It' R f~~~ 0. 500" 0 I - _0 2 —-'. 2 5l - ^ I 4. 8211 -- 22"Figure 3. - Dimensions of Creep-Rupture Sheet Specimen. Figure 3. - Dimensions of Creep-Rupture Sheet Specimen.

Collar bolted to s?-eci- men to sup_-ort extensometer pins Section A - A Sheet Specimenr BJL Extensometer Bars / Bottorn Line of Furnace Spri, to apply tension to bars and mirrors Mirror rotated by bar Figure 4. - Sketch Illustrating Extensometer System 0 n~eX~LS.and Method of Attachment to Sheet So ec. -

50,000 — o R10356 I 12000F 40,000 --- E02326 0 E 1880 -11y 30, 000 1 —- * X25677 1- 1- -- 1 1. 1 A E41024 y. 9 627967 -- -- 20,000 R30409 E1869 P' X46099 X13043 10,000 ____10 ---- 40,000 1350~F 30,000 20,000 * o "ooo. 810,000 - -_J 20,000___ 15000F 2,000 ---- - - 1 1 1 1 1 8,00010 100 1000 Time, hours Figure 5. - Stress - Rupture Time Data Obtained from Ten Heats of Type 321 Sheet Material at 12000, 13500, and 1500~F.

60,000 50,000 5 620809 1 * 620813 1200O~F 40,000 o 636862 / * E40470 o O 30,000 - E41286 I - _ g|E41737 20 000 _______ 7 __III______ _ _ 1' 1___ 2u u ---- E 4X25788 --,. 3X0005 15,000 3X005_ 30,000 a[oJoool *y I 1lilil 1 1 1 IIIIIIDZ1350"F 20,000 /-5-F ~ 0 9, 000 -- I I- I I I I I I I I I I - ------;; 8,000 I I I 1 500 4o' 10,000 5 000 9,000 --— 11111 7,000 -- ---- 6,000- - - - - - - - - - - - - - 5,000 ------ 4,000 ----- — _ - --— A1 I& 1 1 000 Time, hours Figure 6. - Stress-Rupture Data Obtained from Ten Heats of Type 347 Sheet Material at 1200~, 1350~, and 1500~F.

115,000.. - - 1200~F 100,000 _80,000 - ---- 60,000 - - - - 50.000 - -- - ___ —- __ 40,000 ------- - -I —-- --- 30,000 -- - _.1 80,000 o- -- o - 70,000 —---— Rupture } 1350HF -— l ~ 60,000 50,000 ---— A 40,000 5 30,000 1 20,000 -- 50,000 0 Y4474X 40,9-000 - * Y3166X -_ -- - --- -_- ---- A Y4511X ox 20,000 Y4847X- —, _____ —_- A4 E Y4984X A- ~ X 253X X 10,000 Time, hours Figure 7. - Stress-Rupture Data Obtained from Nine Heats of Inconel X Sheet Material at 12000, 13500, and 15000F.

60,000 0 M624 50, 000 o m206 0 M208 -- I 1350~F 40,000 a M207 * M207 38-j 071>l A M733 05 30, 000 ~ M737,9M732 ~ 0 20,000 - M731 0 20,000 -M726 M730 10,000 40, 0000, 1500'F 30,000 20,000 0l_, ooo 9,0 0 - - -f-f.- - - - - - _ _- -/ - / 38, 000 1 10 100 1 00C Time, hours Figure 8. - Stress-Rupture Data Obtained from Ten Heats of N155 Sheet Material at 1350~, 1500~, and ~~1 ~~~~~650F50F 20,000 Time, hours Figure 8. -Stress-Rupture Data Obtained from Ten Heats of N155 Sheet Material at 1350~, 1500-, and

40,000.10.5 - 25% 5 HOURS \ 20 HOURS 80 HOURS 300 OURS 30,000- -fraue -- range ieiart f srl9. 5 2. \'~~~~~110-35% \ f\~~. IN \,0, 000,. -- O, 000 _ _ _ —-- ---- ---- ---- _ __ —--- ---- ---- _ —- -- 10 ---- _4 _ 1150 1350 1550 1150 1350 1550 1150 1350 1550 1150 1350 1550 Temperature, ~F Figure 9. - Summary of Stress-Rupture Strengths for Ten Heats of Type 321 Sheet at 1200~, 1350~, and 1500'F for Time Periods of 5, 20, 80,and 300 Hours. (Note: Percent values shown on graph indicate estimated range in elongation at fracture for specified time period. )

___ ____ ________ 0. V.__ ____ ____ ~7-~4% ___7-__4_ 5 HOURS \ 20 HOURS 80 HOURS 300 HOURS 30,000 A Of- ---- - ----- 3,000- 0 15 -0- 15 -0 10- -1 W20 000 -- -- -- ---- - L. —--- - -— V,, Figure 10. - Summary of Stress-Rupture Strengths for Ten Heats of Type 347 Sheet at 1200~, 1350,, and 1500~F ~ ^ \ \ 5 o-40'r 23-42% d ~ X ~ for000 Hours. (Note: Percent values shown on graph indicate estimated range in elongation at fracture for pecified time period. ) 1150 1350 1550 1150 1350 1550 1150 1350 1550 1150 1350 1550 Temperature, oF Figure 10. - Summary of Stress-Rupture Strengths for Ten Heats of Type 347 Sheet at 1200~, 1350~, and 1500~F for Time Periods of 5, 20, 80, and 300 Hours. (Note: Percent values shown on graph indicate estimated range in elongation at fracture for specified time period.

80,000 — - 5120 HOURS a 5 80 HOURS 300 HOURS 60,000 \ I ~ 1 * \ 10.5-2% m.:o. - o6 05tion 5at fracture fo 0.2 5-.2. 5% 0, 000 20.4 0 --- ---- — 6 e- -- - I - 2-8.5% SS 1150 1350 1550 1150 1350 1550 1150 1350 1550 Temperature, ~F Figure 11. - Summary of Stress-Rupture Strengths for Nine Heats of Inconel X Sheet at 12000, 1350', and 1500'F for Time Periods of 20, 80, and 300 Hours. (Note: Percent values shown on graph indicate estimated range in elongation at fracture for specified time period.)

4 15-26% 1 --- --- --- --- _ —-- --- ------ -----------------------— oo X 5 HCURS 20 HOURS 80 HOURS 300 HOURS ____ Rs__ *9-20% -- 303,000 15 9-18% 6_ 16-34% 20,000 -- - - -- 12. 5-23%0 19-42. k - - 77-21% 16-25^ o- ~ 8-23%4. 10,000'-' 1300 1500 1700 1300 1500 1700 1300 1500 1700 1300 1500 1700 Temperature, ~F Figure 12. - Summary of Stress-Rupture Strengths for Ten Heats of N155 Sheet at 1350', 1500~, and 1650"F for Time Periods of 5, 20,80, and 300 Hours. (Note: Percent values shown on graph indicate estimated range in elongation at fracture for specified time period. )

60, 000' - i-1... 50,000 40,000 ------- 30,000 - 20,000 X -- 610,~~~~~~~~~~1 000 m~o4 0 R10356' I 1, 000a 180 * X25677 AE41024 6.000_ A 627967 6,000 -- -- R30409 -- - E1869 5,000'X46099 - X 13043 4,000 - 34 36 38 40 42 44 46 Parameter x 10-3 Figure 13. - Graph of Stress Vs. Time-Temperature Parameter, P = T(20 + log t), for the Individual Stress-Rupture Tests on Ten Heats of Type 321 Sheet Material at 1200~, 1350~, and 1500~F.

60,000 ------- -- 50,000 40,000 ----- 30,000 - 0 0 — 0 666 0 ~ 20,000 0 —-- * 620813 -- 8,000 - - 0 636862 -, j-~.o - - * E40470 __ a E41286 - AE41887 6,000 --- --- E41737' p' 7X7935 ) X25788 N1 3X0005 4,000 --- 34 36 38' 40 42 44 46 Parameter x 10-3 Figure 14. -Graph of Stress Vs. Time-Temperature Parameter, P = T(20 + log t), for the Individual Stress-Rupture Tests on Ten Heats of Type 347 Sheet Material at 12000, 1350~, and 1500~F

100,000 71- - 0 80, 00o -J-_60,000 _~ _ — 50, 000 * 0* *0g A0 0, 000 ~ 0 10,000 -- o Y4474X * Y3166X ~Y486OX ~ 860,000 A — -- - -— Y451X ---- -- 6,000 P Y4847X 4,000 3 4 3Y6 3 8 40 4 2 44 46 Parameter x 10i Figure 15. - Graph of Stress Vs. Time-Temperature Parameter, P = T (20 + log t), for the Individual StressRupture Tests on Nine Heats of nonel X Sheet Material at 200, 3Y4502, and 1500-F. Material at 1200', 1350~, and 1500~F.

60,000 - - 50,000 - - - - 30,000 --- -- -- ~000: d zo,,ooo I I I,, 0o M624. 3 M206 8,000 0 D-M208 i 2x 071: M733 ~v737 16,000~ g —a M732* M731 M726,,_ M730 4,000 —-- 38 40 42 44 46 48 50 Parameter x 10-3 Figure 16. - Graph of Stress Vs. Time-Temperature Parameter, P = T(20 + log t), for the Individual Stress-Rupture Tests on Ten Heats of N155 Sheet Material at 1350~, 1500~, and 1650~F.

40,000~ — ---- -- - ---- 5 HOURS 20 H )URS 80 HOURS 300 OURS 30,000 __ __ __ __~~~~. _______ _________ _ 20,000 3;; \ \;I I \I \ \ n w~~~~~~~~~~~~~~~~~ G) 0009 0 1150 1350 1550 1150 1350 1550 1150 1350 1550 1150 135Temperature,'F Figure 17. - Summary of 1.0-Percent Total Deformation Strengths for Ten Heats of Type 321 Sheet at 12,0,15" and 1500F for Time Periods of 5 20, 80, and 300 Hours. 10,000 —- - i- --— ^ ---- -- -- -- --- * SA 0~ ~ ~ ~~~~~ ~ -- -- --- - --- - -- — 0 — -- -- ---- -- __ _ Figure 17. -. Summary of 1.0-.Percent Total Deformation Strengths for Ten Heats of Type 31Seta 20,15~ and 1500~F for Time Periods of 5, 20, 80, and 300 Hours.

40,000- } 5 HOURS 20 HOURS 80 HOURS 300 HOUIS 30,000- - - 020~, " 000 -- -- -- -- - - 10O,000 -- -__ -4.-..-'""o~ — t -+ - -- -^. -- I ~ _ 0 -- --- -- -- -- _ _ __ _____ _~ __ 0 0 ___ _- ^ 0~~~~~~~~~~ 1150 1350 1550 1150 1350 1550 1150 1350 1550 1150 1350 1550 Temperature, "F Figure 18. - Summary of 2.0-Percent Total Deformation Strengths for Ten Heats of Type 321 Sheet at 12000, 13500, and 1500~F for Time Periods of 5, 20, 80, and 300 Hours.

40,000 m - - 5 HOURS 20 HOURS 80 HOURS 300 HOURS 30,000 0- -. - - 120,000it —-— t —-— ^ r -- -— \ ---- -; — -- - -- -- -- 20, 000 0~~~~~~~~~~~~SS _ _ _x~5 ____ 0____ 1150 1350 1550 1150 1350 1550 1150 1350 1550 1150 1350 1550 Temperature,'IF Figure 19. - Summary of 2.0-Percent Total Deformation Strengths for Ten Heats of Type 347 Sheet at 1200I, 1350~, and 15002F for Time Periods of 5, 20, 80, and 300 Hours.

40,00 - -- - - 0. 5% DEFORMATION 0. 5% DEFORMATION 0. 2% DEFORMATION 5 HOURS 20 HOURS 5 HOURS 30,000 ---- - -- co~ ~~~0 0- _ ____ -_ _tr, $a. 20" 00 cc\^ ~ \ I 300 1500 1700 1300 1500 1700 1300 1500 1700 1000 - — k -- - — _ - -- -.A 0 -- -- --- -- -- -- --- - -- -- -- -- 1300 1500 1700 1300 1500 1700 1300 1500 1700 Temperature,'F Figure 20. - Summary of 05- and 0. 2-Percent Total Deformation Strengths for Ten Heats of N155 Sheet at 1350~, 1500~, and 1650~F for Time Periods of 5 and 20 Hours.

40,00 5 HOURS 20 HOURS 80 HOURS 300 HOURS 30,000 - - ZO, " XX0001 - - -— 0 10,0000 —----- 1300 1500 1700 1300 1500 1700 1300 1500 1700 1300 1500 1700 Temperature, ~F Figure 21. - Summary of 1. 0-Percent Total Deformation Strengths for Ten Heats of N155 Sheet at 1350~, 1500, and 1650'F for Time Periods of 5, 20, 80, and 300 Hours.

40, — -- 000 - - ad 5 HOURS 20HOURS 80r HOURS 300 HOURS 30,000 -- ---- ---'S2o \oo \ kk 10,000- - -. — 1300 1500 1700 1300 1500 1700 1300 1500 1700 1300 1500 1700 Temperature, ~F Figure 22. - Summary of 2. 0-Percent Total Deformation Strengths for Ten Heats of N155 Sheet at 1350~, 1500~, and 1650~F for Time Periods of 5, 20, 80, and 300 Hours.

60,000 | | T 50,000 - ---- --- ----- - -t- ----- 200~F 30,000. ~ o0 Rupture _A 3 O 20,000 ------ 2.0% Total Deformation - |l 1.0% Total Deformation A 0.5% Total Deformation 1 0 0.2% Total Deformation 10,000 -- - --- 40,000 30,000 - 20,000 1500~F 60,000 20,000 " — 30,000 -- 10,000 8,000,,, 6, 000 AII I1 5,000 I IIII 0. I 1.0 10 100 1003 Time (hours) Figure 23. - Design Data Obtained from Stress-Rupture Tests at 1200~, 1350~, and 1500~F on Type 321 Sheet Material (Heat 627967).

60,000 50,000- I 1200~F 40,000 30,000 4 0.00 0 ___________ ------- __________I ________- ___________I__ 20,000 -0 iORupture * 2. 0% Total Deformation 0 1.0% Total Deformation A 0. 5% Total Deformation 10,000 - _X.0. 2%0 Total Deformation 40,000 1 1,, ____ _ _____ - __III Ii 40,000 1350~F 30, 000 LO,000 -- - ----—. —-- - 30,0000 I I I 1T"V'711111'I I JT'4F' 11111 1 1 1111 1500"F 20,000 A 10 -- 000 8, 000 06,000 5,000 2 0.1 1.0 10 100 000 Time (hours) Figure 24. - Design Data Obtained from Stress-Rupture Tests at 1200', 1350~, and 1500~F on Type 347 Sheet Material (Heat E40470).

1200~F 100, 000 80, OOO 0 Rupture ---.... 60, 000 I 2. 0%Z Total Deformation | iI-_O_50, 000T - D0 1. 0% Total Deformation ___ 40, 000 0.5___ Total Deformation X 0. 2% Total Deformation 30, 000 100, 00 80, 000 1350OF 0,000 _______ ---- 20,000 — - - -— _ 0 40,000 3 0. 0 0 0 ----------- -- -- - - _ _ _ ___________ __ __ _ _ _ _ _ ___________ __ __ _ - _ _ ____________ _ __150 0 " F 0.1 1.0 10 100 1000 F0,000 8,000 6,000 0. I 1.0 10 100 1000 Time (hours) Figure 25. - Design Data Obtained from Stress-Rupture Tests at 1200~, 1350~, and 1500~F on Inconel X Sheet Material (Heat Y4602X).

60,000 50, 000 ~~~~~~~~~40, 000......1 1 J ~~~~~1350"F 30, 000 4 0 — I I T. - _i I________ _ - 2000_o 0 Rupture 1 _-_ * 2.0% Total Deformation O 1.0% Total Deformation A 0.5% Total Deformation X 0.2% Total Deformation 10,000..%Ttl.eoman____.___j.j 40,000 1500~F 30,000 20,000A co j X A OiE10, 000 OO _ J 8,000. 30, 000 1650"F 20,000 6,000 5,000 - 0. 1 1.0 10 100 1000 Time (hours) Figure 26. - Design Data Obtained from Stress-Rupture Tests at 1350~, 1500~, and 1650~F on N155 Sheet Material (Heat M206).