Composite
T300/913C UD tape lamina model inputs (NASA/WWFE reference)
Directional elastic and strength inputs reported for exact T300/913C tape.
Properties
Mechanical
| Property | Value | Unit |
|---|---|---|
| Longitudinal tensile modulus | 138.0 | GPa |
| Transverse tensile modulus | 11.0 | GPa |
| Major Poisson's ratio | 0.28 | - |
| Transverse Poisson's ratio | 0.4 | - |
| In-plane shear modulus | 5.5 | GPa |
| Longitudinal tensile strength | 1500.0 | MPa |
| Longitudinal compressive strength | 900.0 | MPa |
| Transverse tensile strength | 27.0 | MPa |
| Transverse compressive strength | 200.0 | MPa |
| In-plane shear strength | 80.0 | MPa |
Units
Condition
- Condition
- cured T300 carbon-fiber/913C-resin unidirectional tape lamina model
- Temper
- not applicable
- Heat treatment
- cure cycle not reported in the NASA table
- Product form
- unidirectional tape lamina (0-degree tape in the analyzed structure)
- Thickness / diameter range
- ply thickness not reported
- Test direction
- 1 = fiber direction; 2 = in-plane transverse direction; 12 = in-plane shear
- Processing route
- prepreg tape cured into an aircraft laminate; detailed layup and cure are not source-qualified by this card
- Temperature range
- The table does not identify test or model temperature; no temperature extrapolation is allowed.
- Notes
- This card transcribes the T300/913C tape parameters that Raju et al. report from the 1998 World-Wide Failure Exercise for a NASA progressive-failure model. The NASA paper does not present these values as NASA measurements, qualification allowables, batch statistics or supplier guarantees. It identifies tape versus fabric, but does not state ply thickness, fiber volume fraction, resin content, cure cycle, moisture condition or test temperature. Table 1 also prints G_IC as 220 kJ/m^2, a unit/value combination that appears physically suspect; PropLib excludes it rather than silently changing the source.
Standards
No material standards linked.
Record status
- Category
- Composite
- Unit system
- Common SI