Using shock-expansion theory, calculate the lift and drag (in pounds) on a symmetrical diamond airfoil of semiangle \(\varepsilon=15^{\circ}\) (see Fig. 4.35) at an angle of attack to the free stream of \(5^{\circ}\) when the upstream Mach number and pressure are 2.0 and \(2116 \mathrm{lb} / \mathrm{ft}^{2}\), respectively. The maximum thickness of the airfoil is \(t=0.5 \mathrm{ft}\). Assume a unit length of \(1 \mathrm{ft}\) in the span direction (perpendicular to the page in Fig. 4.35).

Figure 4.35: