Fatigue Crack Growth: aluminum_alloy
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.
| material family | alloy designation | C SI (m/cycle per (MPa*sqrt(m))^m) | C units note | KIC MPa sqrtm (MPa*sqrt(m)) | R ratio (dimensionless) | UTS MPa (MPa) | delta Kth MPa sqrtm (MPa*sqrt(m)) | environment | m (dimensionless) | notes | yield strength MPa (MPa) |
|---|---|---|---|---|---|---|---|---|---|---|---|
| aluminum_alloy | 2024-T3 Aluminum | 0 | da/dN in m/cycle; delta_K in MPa*sqrt(m); per Danysc R=1 (R=0.1 in practice near same C) | 36 | 0.1 | 483 | 3.5 | air RT | 3.59 | Standard aluminum alloy R=0 data; high Kth for aluminum; dominant alloy for fuselage skin; C=1.6e-11 m/cycle from Danysc (R=1 note: at R=0.1 similar Paris regime); Kic per MMPDS-11 Table 3.2.3.1.8 | 345 |
| aluminum_alloy | 2024-T3 Aluminum (R=0.5) | 0 | da/dN in m/cycle; delta_K in MPa*sqrt(m); R ratio effect at higher stress ratio | 36 | 0.5 | 483 | 3 | air RT | 3.59 | Same alloy; higher R ratio increases apparent C constant due to Walker parameter (less crack closure); same exponent m | 345 |
| aluminum_alloy | 2024-T851 Aluminum Plate | 0 | da/dN in m/cycle; delta_K in MPa*sqrt(m) | 37 | 0.1 | 476 | 3 | air RT | 3.5 | T851 stress-relieved plate; slightly improved toughness vs T3 sheet; used in thick structural members; Kic from MMPDS-11 | 393 |
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