T650-35 3k (Amoco) carbon fibre (3,000-filament tow) in a 976 (Cytec 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]T
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) | 55.43 – 73.77 | GPa | 12 entriesClick to expand | ||
Compressive Strength(σc) | 176.5 – 903.2 | MPa | 21 entriesClick to expand | ||
Poisson's Ratio(ν)2 entries | 0.03300 n=9, 3 batches | - | 121°C · ETW · 12-axis · [0:f]:7 · as-measured | ||
| ↳ | 0.03000 n=3, 1 batches | - | 121°C · ETW · 12-axis · [90:f]:7 · as-measured | ||
Shear Modulus(G)3 entries | 5.861 range 5.033–6.757n=26, 5 batches, CV 7.1% | GPa | 22°C · RTA · 12-axis · [+/-45:f]:s · not_normalized_ | ||
| ↳ | 7.239 range 6.412–7.791n=30, 5 batches, CV 5.07% | GPa | -55°C · CTA · 12-axis · [+/-45:f]:s · not_normalized_ | ||
| ↳ | 3.241 range 2.551–3.585n=21, 5 batches, CV 9.63% | GPa | 121°C · ETW · 12-axis · [+/-45:f]:s · not_normalized_ | ||
Ultimate Shear Strength(Fsu) | 57.98 – 104.8 | MPa | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 425.4 – 944.6 | MPa | 24 entriesClick to expand | ||
Young's Modulus(E) | 63.64 – 90.32 | GPa | 12 entriesClick to expand | ||