Fatigue Crack Growth in 7050T7451 Aluminium Alloy Thick Section ...

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DSTO-TR-1477Appendix A: QF measurements for the Peened SpecimensTable A-1. Results of the quantitative fractography on KSIF 194, peak stress 360MPaNo. of spectraIARPO3a + 5 markerloadsSimulated FlightHoursMeasurement fromflaw edge to crackpositionmm.Addition of Type IEPS (measured flawdepth)mmAddition of Type IIEPSmm0 0 0.0884 0.0865.5 21282 0.0256 0.114 0.105666.5 21607 0.026 0.1144 0.10668.5 22257 0.0268 0.1152 0.106870.5 22907 0.0276 0.116 0.107672.5 23557 0.0284 0.1168 0.108473.5 23882 0.0292 0.1176 0.109275.5 24531 0.03 0.1184 0.1177.5 25181 0.0308 0.1192 0.110879.5 25831 0.0316 0.12 0.111680.5 26156 0.0328 0.1212 0.112881.5 26481 0.0336 0.122 0.113682.5 26806 0.0344 0.1228 0.114483.5 27131 0.0352 0.1236 0.115284.5 27456 0.0356 0.124 0.115685.5 27781 0.0364 0.1248 0.116486.5 28106 0.0372 0.1256 0.117287.5 28431 0.038 0.1264 0.11888.5 28755 0.0384 0.1268 0.118489.5 29080 0.0396 0.128 0.119690.5 29405 0.0404 0.1288 0.120491.5 29730 0.0416 0.13 0.121692.5 30055 0.0424 0.1308 0.122493.5 30380 0.0432 0.1316 0.123294.5 30705 0.0444 0.1328 0.124495.5 31030 0.0456 0.134 0.125696.5 31355 0.0468 0.1352 0.126897.5 31680 0.0476 0.136 0.127698.5 32005 0.0484 0.1368 0.128499.5 32330 0.05 0.1384 0.13100.5 32654 0.0512 0.1396 0.1312101.5 32979 0.0524 0.1408 0.1324102.5 33304 0.0536 0.142 0.1336103.5 33629 0.0552 0.1436 0.1352104.5 33954 0.0564 0.1448 0.1364105.5 34279 0.0573 0.1457 0.1373106.5 34604 0.0589 0.1473 0.1389107.5 34929 0.0606 0.149 0.1406108.5 35254 0.0622 0.1506 0.1422109.5 35579 0.0648 0.1532 0.1448110.5 35904 0.0672 0.1556 0.1472111.5 36229 0.0697 0.1581 0.1497112.5 36553 0.0721 0.1605 0.1521113.5 36878 0.0743 0.1627 0.1543114.5 37203 0.0772 0.1656 0.1572115.5 37528 0.0805 0.1689 0.1605116.5 37853 0.0831 0.1715 0.1631117.5 38178 0.0886 0.177 0.1686118.5 38503 0.0937 0.1821 0.1737119.5 38828 0.1003 0.1887 0.1803120.5 39153 0.1072 0.1956 0.1872121.5 39478 0.11 0.1984 0.19122.5 39803 0.1193 0.2077 0.1993123.5 40128 0.1279 0.2163 0.2079124.5 40453 0.1374 0.2258 0.2174125.5 40777 0.1476 0.236 0.227636
DSTO-TR-1477126.5 41102 0.1638 0.2522 0.2438127.5 41427 0.1781 0.2665 0.2581128.5 41752 0.1942 0.2826 0.2742129.5 42077 0.2124 0.3008 0.2924130.5 42402 0.2275 0.3159 0.3075131.5 42727 0.253 0.3414 0.333132.5 43052 0.2636 0.352 0.3436133.5 43377 0.2826 0.371 0.3626134.5 43702 0.3103 0.3987 0.3903135.5 44027 0.3313 0.4197 0.4113136.5 44352 0.3623 0.4507 0.4423137.5 44676 0.3973 0.4857 0.4773138.5 45001 0.4284 0.5168 0.5084139.5 45326 0.4709 0.5593 0.5509140.5 45651 0.5195 0.6079 0.5995141.5 45976 0.5801 0.6685 0.6601143.5 46626 0.6817 0.7701 0.7617144.5 46951 0.7435 0.8319 0.8235145.5 47276 0.8181 0.9065 0.8981146.5 47601 0.8897 0.9781 0.9697147.5 47926 0.9878 1.0762 1.0678148.5 48251 1.1356 1.224 1.2156149.5 48576 1.2591 1.3475 1.3391150.5 48900 1.3887 1.4771 1.4687152.5 49550 1.7064 1.7948 1.7864153.5 49875 2.0829 2.1713 2.1629154.5 50200 2.6026 2.691 2.6826155.5 50525 3.4098 3.4982 3.4898156.5 50850 5.4922 5.5806 5.5722Table A-2. Results of the quantitative fractography on KSIF 107, peak stress 360MPaNo. of spectraIARPO3a + 5 markerloadsSimulated FlightHoursMeasurement fromflaw edge to crackpositionmm.Addition of Type IEPS (measured flawdepth)mmAddition of Type IIEPSmm0 0 0.0064 0.008144.5 46951 0.0314 0.0378 0.0394145.5 47276 0.0317 0.0381 0.0397156.5 50850 0.0412 0.0476 0.0492157.5 51175 0.042 0.0484 0.05158.5 51500 0.0431 0.0495 0.0511159.5 51825 0.0438 0.0502 0.0518160.5 52150 0.0449 0.0513 0.0529161.5 52475 0.0453 0.0517 0.0533162.5 52800 0.0464 0.0528 0.0544163.5 53124 0.0468 0.0532 0.0548164.5 53449 0.0476 0.054 0.0556165.5 53774 0.0491 0.0555 0.0571166.5 54099 0.0498 0.0562 0.0578167.5 54424 0.0506 0.057 0.0586168.5 54749 0.051 0.0574 0.059169.5 55074 0.0521 0.0585 0.0601170.5 55399 0.0525 0.0589 0.0605171.5 55724 0.0533 0.0597 0.0613172.5 56049 0.054 0.0604 0.062173.5 56374 0.0552 0.0616 0.0632174.5 56699 0.0559 0.0623 0.0639175.5 57023 0.0567 0.0631 0.0647176.5 57348 0.0579 0.0643 0.0659177.5 57673 0.0586 0.065 0.0666178.5 57998 0.0594 0.0658 0.0674179.5 58323 0.0606 0.067 0.0686180.5 58648 0.0617 0.0681 0.0697181.5 58973 0.0625 0.0689 0.070537
Page 3: Fatigue Crack Growth in 7050T7451 A
Page 8 and 9: DSTO-TR-1477To build the required l
Page 10 and 11: DSTO-TR-1477than internal flaws. An
Page 12 and 13: DSTO-TR-1477127mm Radius (5’)230m
Page 14: DSTO-TR-1477At the surface large gr
Page 18 and 19: DSTO-TR-1477Figure 11 The fracture
Page 20 and 21: DSTO-TR-1477A (KSIF152)B (KSIF107)F
Page 22 and 23: DSTO-TR-1477life axes. The data poi
Page 24 and 25: DSTO-TR-14774. Discussion4.1 Introd
Page 26 and 27: DSTO-TR-14774.2.2 Shape of the crac
Page 28 and 29: DSTO-TR-1477poorly defined areas on
Page 30 and 31: DSTO-TR-1477Simulated flight hours0
Page 33 and 34: DSTO-TR-1477in the appropriate regi
Page 35 and 36: DSTO-TR-1477390MPa(higherslope)420M
Page 37 and 38: DSTO-TR-1477Table 9Specimen No.A co
Page 39 and 40: DSTO-TR-1477considerable concern to
Page 41: DSTO-TR-1477Barter, S. A., Fatigue
Page 45 and 46: DSTO-TR-1477248.5 80743 0.1195 0.12
Page 47 and 48: DSTO-TR-147730.5 9910.1 0.0713 0.10
Page 49 and 50: DSTO-TR-1477104.5 33954 0.0733 0.08
Page 51 and 52: DSTO-TR-147743.5 14134 0.042 0.0468
Page 53 and 54: DSTO-TR-147716.5 5523.6 0.0406 0.05
Page 55 and 56: DSTO-TR-147718.5 6011 0.0264 0.0452
Page 57 and 58: DSTO-TR-147723.5 7635.6 0.0481 0.08
Page 59 and 60: DSTO-TR-1477Table A-13. Results of
Page 61 and 62: DSTO-TR-1477Table A-16. Results of
Page 63 and 64: DISTRIBUTION LISTFatigue Crack Grow
Page 65: Page classification: UNCLASSIFIEDDE

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