The leading edge of a supersonic wing is wedge shaped, with a total wedge angle of 10°. The wing flies at an angle of attack of 3° at an altitude of 10 km in standard atmosphere (k = 1.4 and R = 287 J/kg×K). Assume that the wing is traveling at Mach 2.5 and the total surface area is 1 m2 on each side, i. e., the unit length and the unit width. Required:
a. Schematically draw the wing, including the angle of attack, the oblique shock wave angles, and the upstream properties of Px and Tx.
b. Calculate the pressure in the region above the wing in kPa.
c. Calculate the pressure in the region below the wing in kPa.
d. Calculate the total lift force created by the wing in kN
e. Calculate the total drag force created by the wing in kN.