T650-35 3k (Amoco) carbon fibre (3,000-filament tow) in a 976 (ICI Fiberite) epoxy matrix. Carbon/epoxy is the primary structural composite of modern aerospace: the highest stiffness-to-weight of the common systems, with well-characterised and predictable behaviour. It is used for wing and empennage skins, spars and ribs, fuselage panels and control surfaces — anywhere weight is the governing cost.
Compliance & Regulations
Fiber Direction
Ply Schedule
Laminate Code
[0/0/0/0/0/0/0/0/0/0/0/0]s
Fiber angles relative to the 0° reference direction (red arrow in 3D view). 0° = longitudinal, 90° = transverse, ±45° = shear paths.
| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 53.64 – 73.08 | GPa | 12 entriesClick to expand | ||
Compressive Strength(σc) | 205.5 – 834.3 | MPa | 23 entriesClick to expand | ||
Shear Modulus(G)3 entries | 5.516 range 5.033–6.067n=24, 5 batches, CV 4.9% | GPa | 22°C · RTA · 12-axis · [+/-45]:3s · as-measured | ||
| ↳ | 6.964 range 6.550–7.446n=18, 3 batches, CV 3.82% | GPa | -55°C · CTA · 12-axis · [+/-45]:3s · as-measured | ||
| ↳ | 3.516 range 3.241–3.723n=22, 5 batches, CV 3.73% | GPa | 121°C · ETW · 12-axis · [+/-45]:3s · as-measured | ||
Ultimate Shear Strength(Fsu) | 67.02 – 122.0 | MPa | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 354.4 – 861.8 | MPa | 22 entriesClick to expand | ||
Young's Modulus(E) | 63.16 – 85.49 | GPa | 12 entriesClick to expand | ||