Specification for aircraft material. 12 per cent chromium corrosion-resisting steel (35/45 tonf/sq in: limiting ruling section 6 in)
Elements | Min.(≥) | Max.(≤) | Similar | Remarks |
---|---|---|---|---|
C | - | 0.12 | ||
Si | - | 0.80 | ||
Mn | - | 1.00 | ||
P | - | 0.030 | ||
S | - | 0.025 | ||
Cr | 11.50 | 13.50 | ||
Ni | - | 1.00 | ||
Mo | - | - | ||
Nb/Ti | - | - |
Specification for aircraft material. 12 per cent chromium corrosion-resisting steel (35/45 tonf/sq in: limiting ruling section 6 in)
Proof strength Rp0.2 (MPa) |
Tensile strength Rm (MPa) |
Impact energy KV (J) |
Elongation at fracture A (%) |
Reduction in cross section on fracture Z (%) |
As-Heat-Treated Condition | Brinell hardness (HBW) |
---|---|---|---|---|---|---|
692 (≥) | 547 (≥) | 22 | 34 | 32 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 413 |
Property | Density kg/dm3 |
Temperature T °C/F |
Specific heat J / kgK |
Thermal conductivity W/mK |
Electric resistance µΩ·cm |
Modulus of elasticity kN/mm2 |
Expansion rate |
---|---|---|---|---|---|---|---|
373 (≥) | 211 (≥) | 14 | 42 | 33 | Solution and Aging, Annealing, Ausaging, Q+T,etc | 144 | |
Temp. °C/°F |
Creep strain limit (10000h) (Rp1,0) N/mm2 |
Creep rupture strength (10000h) (Rp1,0) N/mm2 |
|||||
749 | 485 | 452 |
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