Question: Use the shock-expansion method to solve for the lift and drag coefficients of the cross-section of the Saturn 1-B fin shown in Fig. as functions of angle of attack from -5 to 5 degrees at Mach 2. Representative dimensions (the chord of the fin varies with spanwise position, so consider just the airfoil shape) are presented in the figure below. Assume that the pressure on the base of the fin is zero.
