Composite Wingy

1️⃣ Wing design

Wing CAD Model
Span 5643 mm
Root chord 2752 mm
Tip chord 1297 mm
Front sweep 10.388 °
Rib increment 20 mm

2️⃣ Wing Load Calculation

3️⃣ Composite Materials Properties

Properties Comparison

Property ROMInverse ROMHalpin-TsaiHashin-Rosen
E1 (GPa) 128.390 9.130 9.130 128.416
E2 (GPa) 6.954 9.012 7.963 4.803
G12 (GPa) 3.252 5.190 5.199 4.574 4.574 5.640
nu12 (-) 0.263 0.263 0.245
nu21 (-) 0.018
128.390 [GPa]

Young's longitudinal modulus (E1)

E1=E1fVf+EmVmE_1 = E_{1f}V_f + E_mV_m

single property chart

6.954 [GPa]

Young's transverse modulus (E2)

E2=E2f⋅EmEm⋅Vf+E2f⋅VmE_2 = \frac{E_{2f} \cdot E_m}{E_m \cdot V_f + E_{2f} \cdot V_m}

single property chart

3.252 [GPa]

Shear modulus (G12)

G12=G12fGmVfGm+VmG12fG_{12} = \frac{G_{12f} G_m}{V_f G_m + V_m G_{12f}}

single property chart

0.263 [-]

Poisson's major ratio (nu12)

ν12=ν12fVf+νmVm\nu_{12} = \nu_{12f}V_f + \nu_mV_m

single property chart

0.018 [-]

Poisson's minor ratio (nu21)

ν21=E2E1ν12\nu_{21} = \frac{E_2}{E_1} \nu_{12}

single property chart

4️⃣ Failure Criteria

Failure criteria analysis will be implemented here.