Celion 12k (Celanese) carbon fibre (12,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as tape. 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]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) | 18,100 – 25,100 | ksi | 7 entriesClick to expand | ||
Compressive Strength(σc) | 158 – 267 | ksi | 7 entriesClick to expand | ||
Elongation at Break(εf) | 0.9210 – 1.580 | - | 5 entriesClick to expand | ||
Poisson's Ratio(ν)3 entries | 0.2860 n=5, 1 batches | - | 24°C · RTA · 12-axis · [0]:5 · as-measured | ||
| ↳ | 0.2920 n=5, 1 batches | - | 24°C · RTW · 12-axis · [0]:5 · as-measured | ||
| ↳ | 0.3220 n=5, 1 batches | - | 82°C · ETW · 12-axis · [0]:5 · as-measured | ||
Ultimate Shear Strength(Fsu)4 entries | 9.900 range 9.300–11.10n=20, 1 batches, CV 4.16% | ksi | 24°C · RTA · 12-axis · [+-45/45]:s · as-measured | ||
| ↳ | 10.00 range 8.100–11.10n=5, 1 batches, CV 11.7% | ksi | 82°C · ETA · 12-axis · [+-45/45]:s · as-measured | ||
| ↳ | 12.00 range 11.30–12.30n=5, 1 batches, CV 3.41% | ksi | 24°C · RTW · 12-axis · [+-45/45]:s · as-measured | ||
| ↳ | 10.00 range 8.200–11.40n=5, 1 batches, CV 11.7% | ksi | 82°C · ETW · 12-axis · [+-45/45]:s · as-measured | ||
Ultimate Tensile Strength(σUTS) | 5.210 – 387 | ksi | 9 entriesClick to expand | ||
Young's Modulus(E) | 1,190 – 23,000 | ksi | 9 entriesClick to expand | ||