Consider a flat plate at an angle of attack in a viscous supersonic flow; i.e., there is both skin friction drag and wave drag on the plate. Use linear theory for the lift and wave-drag coefficients. Denote the total skin friction drag coefficient by C_{f }, and assume that it does not change with angle of attack.

(a) Derive the expression for the angle of attack at which maximum lift-to-drag ratio occurs as a function of C _{f }and freestream Mach number.

(b) Derive the expression for the maximum lift-to-drag ratio as a function of C _{f} and freestream Mach number M.

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