2. For the double-wedge airfoil shown below, the incoming air is at a Mach number of 3 with a static pressure of 40 kPa. Do NOT consider the flow region behind the trailing edge of the airfoil; only consider the incoming flow region and the regions directly above and below the airfoil. Answer the following: M = 3 Po 40 kPa $10 0.8m a. Sketch the flow pattern for this configuration, i.e., clearly draw oblique shocks / expansion fans where necessary and illustrate the flow path including the angles of the flow (with respect to the horizontal). b. How does the static pressure vary over the surface of the airfoil? c. Determine the lift and drag per meter span acting on the airfoil.