Print Email Facebook Twitter Flight simulation fatigue crack propagation evaluation of candidate lower wing skin materials with particular consideration of spectrum truncation Title Flight simulation fatigue crack propagation evaluation of candidate lower wing skin materials with particular consideration of spectrum truncation Author Wanhill, R.J.H. Institution National Aerospace Laboratory NLR Date 1977-07-01 Abstract Flight simulation fatigu-e crack propagation tests were carried out on 2024-T3, 7475-T761 and mill annealed Ti-6A1-4V sheet in thicknesses up to 3 miri and representative for transport aircraft lower wing skin stiffened panels of end load capacities 1.5 and 3 MN/m. The performance of 2024-T3 was much superior, owing mainly to greater retardation of crack growth after severe flights. The effect of load truncation was also greater for 2024-T3. The significance of the results for the choice of advanced structural concepts and materials and the choice of truncation level is discussed. A recommendation for further investigation is given. Subject load testsfatigue crack propagationaluminium alloystitanium alloygust loadscrack propagationfatigue (materials)fatigue testsretardationwing panelsstiffening To reference this document use: http://resolver.tudelft.nl/uuid:37211d98-bb14-42bb-b71c-85beb797a70c Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 77092 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1977 National Aerospace Laboratory NLR Files PDF NLR_TR_77092_U.pdf 13.69 MB Close viewer /islandora/object/uuid:37211d98-bb14-42bb-b71c-85beb797a70c/datastream/OBJ/view