The aircraft members are made of aluminum (G = 27.0 GPa) and have a length of 1.0 m, unles...

The aircraft members are made of aluminum (G = 27.0 GPa) and have a length of 1.0 m, unless otherwise stated. Assume that the stress concentrations at corners are negligible.

The allowable shear stress in the torsion member, whose cross section is shown in Figure P6.46, is 60 MPa. Determine the design torque for the member.

FIGURE P6.46