By Theodore Von Kármán
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Thus, fatigue-crack-growth rate behavior can be characterized, in general form, by the relation da/dN . ). 3(a) may be simplified to da/dN . 3(b)] where Kmax ∆K ∆K = = = the maximum cyclic stress-intensity factor (1-R)Kmax, the range of the cyclic stress-intensity factor, for R $ 0 Kmax, for R # 0. 3(b) becomes da/dN . ∆a/∆N = g(∆K, R). 3 Fatigue Crack Growth Data Presentation — Fatigue crack growth rate data for constant amplitude cyclic loading conditions are presented as logarithmic plots of da/dN versus ∆K.
This nonlinearity results from the alleviation of stress at the crack tip by causing plastic deformation. 4. Typical load-deformation record for non-plane strain fracture. 1 Analysis of Plane-Stress and Transitional-Stress State Fracture — The basic concepts of linear elastic fracture mechanics as used in plane-strain fracture analysis also applies to these conditions. 2, is used to relate load or stress, flaw size, component geometry, and fracture toughness. However, interpretation of the critical flaw dimension and corresponding stress has two possibilities.
Condition . . . . . . . Thickness, in. . . . . . Basis . . . . . . . . Mechanical Properties: Ftu , ksi: L ................ LT . . . . . . . . ST . . . . . . . . Fty, ksi: L ................ LT . . . . . . . . ST . . . . . . . . Fcy, ksi: L ................ LT . . . . . . . . ST . . . . . . . . Fsu , ksi . . . . . . . 5) . . . . . 0) . . . . . 5) . . . . . 0) . . . . . e, percent: L ................
Aerodynamics by Theodore Von Kármán