T650-35 (ICI Fiberite) carbon fibre (12,000-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]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)3 entries | 9.515 range 8.481–9.928n=9, 3 batches, CV 5.48% | GPa | 22°C · RTA · 2-axis · [90]:22 · as-measured | ||
| ↳ | 10.69 range 9.997–11.45n=8, 3 batches, CV 4.11% | GPa | -55°C · CTA · 2-axis · [90]:22 · as-measured | ||
| ↳ | 7.446 range 6.481–8.343n=10, 3 batches, CV 8.38% | GPa | 121°C · ETW · 2-axis · [90]:22 · as-measured | ||
Compressive Strength(σc) | 105.5 – 307.5 | MPa | 5 entriesClick to expand | ||
Shear Modulus(G)3 entries | 5.137 range 4.688–5.723n=30, 5 batches, CV 4.82% | GPa | 22°C · RTA · 12-axis · [+/-45]:4s · as-measured | ||
| ↳ | 6.336 range 4.826–7.239n=30, 5 batches, CV 10.4% | GPa | -55°C · CTA · 12-axis · [+/-45]:4s · as-measured | ||
| ↳ | 3.737 range 3.516–3.999n=30, 5 batches, CV 3.91% | GPa | 121°C · ETW · 12-axis · [+/-45]:4s · as-measured | ||
Ultimate Shear Strength(Fsu) | 59.09 – 132.4 | MPa | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 0.00910 – 2.034 | GPa | 16 entriesClick to expand | ||
Young's Modulus(E) | 5.654 – 171.0 | GPa | 9 entriesClick to expand | ||