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) | 8,040 – 10,700 | ksi | 12 entriesClick to expand | ||
Compressive Strength(σc) | 25.60 – 131 | ksi | 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 | 850 range 730–980n=26, 5 batches, CV 7.1% | ksi | 22°C · RTA · 12-axis · [+/-45:f]:s · not_normalized_ | ||
| ↳ | 1,050 range 930–1,130n=30, 5 batches, CV 5.07% | ksi | -55°C · CTA · 12-axis · [+/-45:f]:s · not_normalized_ | ||
| ↳ | 470 range 370–520n=21, 5 batches, CV 9.63% | ksi | 121°C · ETW · 12-axis · [+/-45:f]:s · not_normalized_ | ||
Ultimate Shear Strength(Fsu) | 8.410 – 15.20 | ksi | 6 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 61.70 – 137 | ksi | 24 entriesClick to expand | ||
Young's Modulus(E) | 9,230 – 13,100 | ksi | 12 entriesClick to expand | ||