Celion 12k (Celanese) carbon fibre (12,000-filament tow) in a 938 (Fiberite) 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. The handbook characterises it from -67 °F to 250 °F, consistent with moderately elevated service. MatWorld carries 14 tensile, compressive and shear curves for this system, digitised from MIL-HDBK-17-2F Volume 2 (US Government work, public domain).
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.
11 interactive curves for this material
Stress-strain, S-N fatigue and environmental knockdown curves are free with an account.
Create free account| Property | Value | Unit | Conditions | Source | |
|---|---|---|---|---|---|
Compressive Modulus(Ec) | 14,700 – 23,700 | ksi | 10 entriesClick to expand | ||
Compressive Strength(σc) | 157 – 286 | ksi | 10 entriesClick to expand | ||
Elongation at Break(εf) | 0.1300 – 1.610 | - | 9 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS) | 18.30 range 16.60–19.70n=102, 3 batches, CV 3.29% | ksi | 24°C · RTA · 13-axis · [0]:14 · as-measured | ||
Poisson's Ratio(ν) | 0.2790 – 0.3450 | - | 5 entriesClick to expand | ||
Ultimate Shear Strength(Fsu) | 11.00 – 18.00 | ksi | 5 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 5.000 – 337 | ksi | 14 entriesClick to expand | ||
Young's Modulus(E) | 940 – 23,400 | ksi | 14 entriesClick to expand | ||