Aerospace Materials: HASTELLOY X SHEET PLATE ST
Aerospace material mechanical properties and design allowables at ambient, elevated, and cryogenic temperatures per MMPDS-11 (Metallic Materials Properties Development and Standardization). Covers primary structural alloys: aluminum (2024-T3, 7075-T6, 6061-T6, 2219-T87), titanium (Ti-6Al-4V), nickel superalloys (Inconel 718), and steels (300M, 4130, 4340).
| material id | temp f | E Msi (Msi) | Ec Msi (Msi) | Ftu ksi LT (ksi) | Fty ksi LT (ksi) | G Msi (Msi) | basis | condition | density lb in3 (lb/in^3) | elongation pct LT (%) | form | poisson ratio | specification | thickness range |
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| HASTELLOY X SHEET PLATE ST 0.010-0.020-0.100 0.019 A | 70 | 29.8 | 29.8 | 102 | 44 | 11.3 | A | Solution treated (annealed) | 0.297 | 35 | Sheeta and plate | 0.32 | AMS 5536 | 0.010-0.020-0.100 0.019 |
| HASTELLOY X SHEET PLATE ST 0.010-0.020-0.100 0.019 S T6 3 1 0b C1 | 70 | 29.8 | 29.8 | 105 | 45 | 11.3 | S | Solution treated (annealed) | 0.297 | — | Sheeta and plate | 0.32 | AMS 5536 | 0.010-0.020-0.100 0.019 |
| HASTELLOY X SHEET PLATE ST 0.010-0.020-0.100 0.019 S T6 3 1 0b C2 | 70 | 29.8 | 29.8 | 105 | 45 | 11.3 | S | Solution treated (annealed) | 0.297 | 29 | Sheeta and plate | 0.32 | AMS 5536 | 0.010-0.020-0.100 0.019 |
| HASTELLOY X SHEET PLATE ST 0.101-0.187 B | 70 | 29.8 | 29.8 | 106 | 47 | 11.3 | B | Solution treated (annealed) | 0.297 | — | Sheeta and plate | 0.32 | AMS 5536 | 0.101-0.187 |
| HASTELLOY X SHEET PLATE ST 0.101-0.187 S | 70 | 29.8 | 29.8 | 105 | 45 | 11.3 | S | Solution treated (annealed) | 0.297 | 35 | Sheeta and plate | 0.32 | AMS 5536 | 0.101-0.187 |
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