Celion 3000 (Celanese) carbon fibre (3,000-filament tow) in an E7K8 (U.S. Polymeric) epoxy matrix, supplied as plain weave. 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 -65 °F to 180 °F, consistent with ambient and mildly elevated service. MatWorld carries 11 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
[0/0/0/0/0/0/0/0/0/0]s
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) | 51.78 – 71.02 | GPa | 24 entriesClick to expand | ||
Compressive Strength(σc) | 486.1 – 958.4 | MPa | 24 entriesClick to expand | ||
Elongation at Break(εf) | 0.7620 – 12.30 | - | 18 entriesClick to expand | ||
Interlaminar Shear Strength(ILSS) | 45.51 – 93.77 | MPa | 12 entriesClick to expand | ||
Poisson's Ratio(ν) | 0.05600 – 0.06200 | - | 5 entriesClick to expand | ||
Ultimate Tensile Strength(σUTS) | 0.6784 – 1.062 | GPa | 24 entriesClick to expand | ||
Young's Modulus(E) | 58.67 – 78.60 | GPa | 24 entriesClick to expand | ||