Consider two-dimensional flow over the double-wedge airfoil shown below. a. Sketch the flow pattern with any shocks and expansion fans. Assume flow returns to freestream direction in the wake. b. Determine the pressure acting along each six segments of the airfoil surface. Use "2", "3", "4" for upper surface (starting from leading edge), and "5", "6", "7" for lower surface (starting from leading edge). c. Determine the lift and drag force per unit span (L' and D') acting on the airfoil. d. Determine the lift and drag coefficients (C) and C) for the airfoil. M=3 p=20 kPa 0.2 m 15 10 0.2 m 15