Print Email Facebook Twitter Effects of crack plane orientation transitions on flight simulation fatigue crack propagation in a high strength aluminium alloy (7050) Title Effects of crack plane orientation transitions on flight simulation fatigue crack propagation in a high strength aluminium alloy (7050) Author Wanhill, R.J.H. Schra, L. Institution National Aerospace Laboratory NLR Date 1976-10-01 Abstract The effects of flat to slant fracture transitions on flight simulation fatigue crack propagation in specimens of 7O5O aluminium alloy forgings are discussed. For specimens containing flat, shearlipped, or full slant fractures at similar crack lengths the crack resistance (R curve) approach appears to provide an explanation for differences in the static crack growth increments induced by peak loads. The results emphasize the complexity of fatigue under realastic loading and add another variable to environmental effects. Subject aluminum alloysshear stressfatiguecrack propagationflight-simulationforgingrandom loadsgust loadsfatigue testsaircraft maneuversfractographyfracture strength To reference this document use: http://resolver.tudelft.nl/uuid:640a9b72-ddbe-43b0-be9c-6e57d4461c28 Publisher Nationaal Lucht- en Ruimtevaartlaboratorium Access restriction Campus only Source NLR-TR 76130 U Part of collection Aerospace Engineering Reports Document type report Rights (c) 1976 National Aerospace Laboratory NLR Files PDF NLR_TR_76130_U.pdf 8.37 MB Close viewer /islandora/object/uuid:640a9b72-ddbe-43b0-be9c-6e57d4461c28/datastream/OBJ/view