Aluminum 7150 T61511
Temper
AA 7150 · UNS A97150 · EN AW-7150
T61511 = near-peak aged extrusion, stretched and stress-relieved
Extruded stringer/spar temper combining very high strength with controlled residual stress for straight machined profiles.
Values for the T61511 condition
Other 7150 tempers and conditions
7150 is listed in 6 conditions; see the grade overview at 7150.
Compare all 6 conditionsHide
| Condition · open for datasheet | Best for | Yield MPa | Tensile MPa | Elong. % | Hardness | Conductivity |
|---|---|---|---|---|---|---|
Overaged (T77 practice), stretched and stress-relieved plate | Choose when short-transverse SCC and exfoliation resistance must be improved while keeping ~90 % of peak strength. | 517 | 565 | 11 | 160 HB | 40 % IACS |
Modified near-peak age with stretch stress relief | Near-peak aged plate temper giving slightly better toughness/exfoliation behaviour than T651 at almost the same strength; used on upper wing skins. | 565 | 600 | 10 | 170 HB | 35 % IACS |
T651Default T6, stress relieved by stretching | Standard peak-aged, low-residual-stress plate temper for machined aerospace structure. | 572 | 620 | 10 | 175 HB | 33 % IACS |
Solution heat treated and artificially aged | Maximum strength condition for parts where SCC exposure and residual stress are controlled by design. | 579 | 621 | 10 | 175 HB | 33 % IACS |
Overaged extrusion, stretched and stress-relieved | Extruded stringers/frames needing high strength together with good exfoliation and SCC resistance. | 586 | 621 | 10 | 172 HB | 39 % IACS |
T61511This page Near-peak aged extrusion, stretched and stress-relieved | Extruded stringer/spar temper combining very high strength with controlled residual stress for straight machined profiles. | 600 | 634 | 9 | 180 HB | 34 % IACS |
What is 7150 T61511?
7150 T61511 is 7150 in the T61511 temper — extruded stringer/spar temper combining very high strength with controlled residual stress for straight machined profiles. 7150 T61511 has a yield strength of 600 MPa (87 ksi) and a tensile strength of 634 MPa (92 ksi) — stronger than 98% of aluminum grades. Elongation at break is 9% and the elastic modulus is 71 GPa (10.3 Msi). 7150 T61511 has a density of 2.82 g/cm³ (0.102 lb/in³), heavier than 89% of aluminum grades. It melts at 477°C (891 °F). T651 is the default condition FabDigit quotes; T61511 is available on request or by drawing note.
Advantages
- High strength — 600 MPa (87 ksi), better than 98% of aluminum grades
Limitations
- Difficult to weld — 15/100, worse than 96% of aluminum grades
- Needs corrosion protection — 34/100, worse than 89% of aluminum grades
- Limited service temperature — 120°C (248 °F), worse than 79% of aluminum grades
7150 T61511 properties
Typical room-temperature values for 7150 T61511; 22 are specific to this condition. Other listed values are 7150 reference data and may not represent this condition. Bars are the position among aluminum grades.
Physical3
7150 T61511 has a density of 2.82 g/cm³ (0.102 lb/in³), heavier than 89% of aluminum grades. It melts at 477°C (891 °F).
Mechanical12
7150 T61511 has a yield strength of 600 MPa (87 ksi) and a tensile strength of 634 MPa (92 ksi) — stronger than 98% of aluminum grades. Elongation at break is 9% and the elastic modulus is 71 GPa (10.3 Msi).
Thermal6
7150 T61511 is rated for continuous service to 120°C (248 °F). It conducts heat at 134 W/m·K (77.4 BTU/hr·ft·°F), worse than 60% of aluminum grades. Thermal expansion is 23.4 µm/m·K (13 µin/in·°F).
Electrical3
7150 T61511 conducts electricity at 34 % IACS, worse than 52% of aluminum grades.
Chemical & Environmental3
Corrosion resistance is poor (34/100), worse than 89% of aluminum grades.
Sustainability4
Producing a kilogram of 7150 T61511 takes about 205 MJ of energy and emits 12.5 kg of CO₂ — more than 76% of aluminum grades. Typical recycled content is 5%.
Manufacturability7
7150 T61511's machinability is very good (70/100, better than 72% of aluminum grades); weldability poor (15/100); formability poor (18/100).
Values are nominal handbook figures for design screening. Confirm any required mill or lot documentation when quoting.
Working with 7150 T61511
Is 7150 easy to machine?
Machines very freely with sharp polished-flute carbide tooling, high speed and copious coolant; watch part distortion from residual stress in thick plate — prefer stretched (T651/T7751) stock and symmetric roughing passes.
Can 7150 be welded?
Not weldable by conventional MIG/TIG (hot cracking and severe HAZ strength loss); join by riveting, bolting or bonding — friction stir welding is feasible with qualified parameters.
Can 7150 be formed, bent or molded?
Form in the freshly quenched W condition or before aging; peak-aged plate has very limited cold formability and large minimum bend radii.
What surface finishes work on 7150?
Chromic or sulfuric anodize plus epoxy primer is the standard aerospace protection; shot peening and clad or Alclad layers improve fatigue and exfoliation resistance.
7150 chemical composition (wt %)
Limits by weight percent from the governing specification, written the way the spec states them — a single maximum for impurities, a range for alloying elements, and the base element as balance. Nominal is the typical mid-range value.
| Element | Spec limit (wt %) | Nominal |
|---|---|---|
| Si | ≤ 0.12 | — |
| Fe | ≤ 0.15 | — |
| Cu | 1.9 – 2.5 | 2.2 |
| Mn | ≤ 0.1 | — |
| Mg | 2 – 2.7 | 2.3 |
| Cr | ≤ 0.04 | — |
| Zn | 5.9 – 6.9 | 6.4 |
| Ti | ≤ 0.06 | — |
| Zrdispersoid former, suppresses recrystallisation | 0.08 – 0.15 | 0.11 |
| Others (each) | ≤ 0.05 | — |
| Others (total) | ≤ 0.15 | — |
| Al | balance | — |
7150 T61511 — frequently asked
What is 7150 T61511 used for?
7150 T61511 is typically used for upper wing skins, spar caps and wing stringers, machined aerospace fittings, fuselage frames and bulkheads, high-load structural brackets and thick-plate machined airframe components. In short: premium 7000 series; higher strength than 7075.
What is the yield strength of 7150 T61511?
7150 T61511 has a typical yield strength of 600 MPa (87 ksi) and a tensile strength of 634 MPa (92 ksi) — stronger than 98% of aluminum grades. Strength varies by condition: see the 6 listed tempers.
Is 7150 T61511 easy to machine?
Yes — machinability is rated very good (70/100, better than 72% of aluminum grades). Machines very freely with sharp polished-flute carbide tooling, high speed and copious coolant; watch part distortion from residual stress in thick plate — prefer stretched (T651/T7751) stock and symmetric roughing passes.
Can 7150 T61511 be welded?
Not readily — weldability is rated poor (15/100). Not weldable by conventional MIG/TIG (hot cracking and severe HAZ strength loss); join by riveting, bolting or bonding — friction stir welding is feasible with qualified parameters.
What surface finishes work on 7150 T61511?
Chromic or sulfuric anodize plus epoxy primer is the standard aerospace protection; shot peening and clad or Alclad layers improve fatigue and exfoliation resistance.
Can 7150 T61511 be formed, bent or molded?
Form in the freshly quenched W condition or before aging; peak-aged plate has very limited cold formability and large minimum bend radii.
What is the maximum service temperature of 7150 T61511?
7150 T61511 is rated for continuous use to about 120°C (248 °F). Strength falls off well before that limit — check the elevated-temperature data for load-bearing parts.
What is the difference between 7150-T651 and 7150-T7751?
T651 is the default condition — standard peak-aged, low-residual-stress plate temper for machined aerospace structure. T7751: choose when short-transverse SCC and exfoliation resistance must be improved while keeping ~90 % of peak strength. Yield strength is 572 MPa in T651 versus 517 MPa in T7751.
Can FabDigit make parts in 7150 T61511?
Yes — 7150 T61511 is available for CNC machining and sheet metal; every part is priced by an engineer rather than instantly. Upload a STEP file to get a price and a DFM check.
Sources
- International Alloy Designations and Chemical Composition Limits for Wrought Aluminum (Teal Sheets) — The Aluminum Association (2018)
- MMPDS-17 Metallic Materials Properties Development and Standardization — Battelle/FAA (2022)
- ASM Handbook Vol.2: Properties and Selection — Nonferrous Alloys — ASM International (1990)
- ASM Handbook Vol.19: Fatigue and Fracture — ASM International (1996)
- AMS 4252 / AMS 4306 series (7150 plate and extrusion) — SAE International (2018)
- High-strength 7000-series aerospace plate and extrusion data — Alcoa / Arconic / Constellium (2020)
Property data is compiled from published supplier and standards handbooks and normalised for comparison. Nothing on this page is a certification — request mill certs, CoC or material test reports with your order.