Fatigue Crack Growth

Paris Law fatigue crack growth constants (C and m) for engineering alloys at stress ratio R=0.1 in air at room temperature. Provides da/dN = C * delta_K^m where da/dN is crack growth rate in m/cycle and delta_K is stress intensity factor range in MPa*sqrt(m). Also includes threshold stress intensity range delta_Kth (MPa*sqrt(m)), plane-strain fracture toughness KIC (MPa*sqrt(m)), yield strength, and UTS. Covers structural steels (A36, A514, 4340, 300M, 4130, HY-80), stainless steels (304, 316, 316L, 17-4PH, 2205 duplex), aluminum alloys (2024-T3, 7075-T6, 7075-T651, 6061-T6, 6061-T651, 2219-T87, 7050-T7452, 2024-T851, 5083-H116), titanium alloys (Ti-6Al-4V annealed/STA/EB-welded/LPBF, Ti-3Al-2.5V, Ti-10V-2Fe-3Al), and nickel superalloys (Inconel 718 annealed/STA, Inconel 625, Waspaloy, Hastelloy C-276). Data from NASGRO database, AFGROW, MMPDS-11, Dowling, and ASM Handbook Vol.19.