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) | 7,780 – 10,600 | ksi | 12 entriesClick to expand | ||
Compressive Strength(σc) | 29.80 – 121 | ksi | 23 entriesClick to expand | ||
Shear Modulus(G)3 entries | 800 range 730–880n=24, 5 batches, CV 4.9% | ksi | 22°C · RTA · 12-axis · [+/-45]:3s · as-measured | ||
| ↳ | 1,010 range 950–1,080n=18, 3 batches, CV 3.82% | ksi | -55°C · CTA · 12-axis · [+/-45]:3s · as-measured | ||
| ↳ | 510 range 470–540n=22, 5 batches, CV 3.73% | ksi | 121°C · ETW · 12-axis · [+/-45]:3s · as-measured | ||
Ultimate Shear Strength(Fsu) | 9.720 – 17.70 | ksi | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 51.40 – 125 | ksi | 22 entriesClick to expand | ||
Young's Modulus(E) | 9,160 – 12,400 | ksi | 12 entriesClick to expand | ||