Consider a diamond-wedge airfoil such as shown in Figure 9.24, with a half-angle = 10. The

Consider a diamond-wedge airfoil such as shown in Figure 9.24, with a half-angle ε = 10°. The airfoil is at an angle of attack α = 15° to a Mach 3 free stream. Using linear theory, calculate the lift and wave-drag coefficients for the airfoil. Compare these approximate results with those from the exact shock-expansion theory obtained in Prob. 9.14.