We apply wave-field theory to the half diamond airfoil in supersonic flow, as shown. Assuming that the flow downstream of the shock is irrotational, we may use the irrotational MOC at the shoulder...

We apply wave-field theory to the half diamond airfoil in supersonic flow, as shown. Assuming that the flow downstream of the shock is irrotational, we may use the irrotational MOC at the shoulder with two C₊
characteristics, AB and AC. Mach number in region 2 is M₂
= 2.0 and the flow angle is θ2 = +4◦. The flow angles in regions 3 and 4 are θ₃
= 0◦ and θ₄
= −4◦ respectively. Calculate:

(a) Mach numbers in regions 3 and 4

(b) The angles that C₊
characteristics make with respect to the x-axis

(c) Flight Mach number, M₁