Problem $2-[5$ points$]$

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 $(L^{\text{'}}$ and $D^{\text{'}})$ acting on the airfoil.

d$.$ Determine the lift and drag coefficients and $($:$C_d$