Durability Methods Development. Volume 8. Test and Fractography Data
Final rept. Jun 1979-Aug 1982
GENERAL DYNAMICS FORT WORTH TX FORT WORTH DIV
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This report contains the test results and raw fractography data for Phase II of the Durability Methods Development program. The fractography data in this report can be used to quantify the initial fatigue quality or equivalent initial flaw size EIFS cumulative distribution for clearance-fit fastener holes. These data can be used to implement the probabilistic fracture mechanics approach, described in the Durability Design Handbook AFFDL-TR-83-3027, for durability analysis. Over 700 specimens were fatigue tested in Phase II. Variables included in the test program were material 7475-T7351 and 2024-T851 aluminum D6ac steel, spectrum F-16 400 hour and F-16 500 hour B-1 bomber stress level, fastener diameterfit, bolt load transfer 0,15, 39, 40 and specimen geometry. Most of the fatigue data was obtained for 7475-T7351 aluminum, F-16 400 hour spectrum and countersunk fastener holes. Fractography data are presented for over 800 fatigue cracks primary and secondary in fastener holes. A tear-down inspection of the F-16 durability test article wing is documented, including fractographic results for the lower wing skins.
- Attack and Fighter Aircraft
- Metallurgy and Metallography