A cross section of the leading edge of an airplane wing is shown in Figure P6.111. The enclosed area is 82 in. 2 . Sheet thicknesses are shown on the diagram. For an applied torque of T = 100 kip-in.,...

A cross section of the leading edge of an airplane wing is shown in Figure P6.111. The enclosed area is 82 in.². Sheet thicknesses are shown on the diagram. For an applied torque of T = 100 kip-in., determine the magnitude of the maximum shear stress developed in the section. (Note: The dimensions shown are measured to the wall centerline.)