Please answer as soon as possible, thanks! 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 $($C$\_$l$.$ and $.$C$\_$d$)$ for the airfoil.