The mean dimensions of the cross section of the leading edge and torsion box of an airplane wing can be approximated as shown. If the wing is made of a composite having an allowable shear stress of Tallow = 50 MPa and the wall thickness is 8 mm, determine the maximum allowable torque and the corresponding angle of twist per meter length of the wing. Take G = 30 GPa. 8 mm J0.25 m [0.25 m 0.8 m 8 mm- 8 mm 2 m