For the diamond-wedge airfoil shown below, the incoming Mach number of the flow

Question

For the diamond-wedge airfoil shown below, the incoming Mach number of the flow is 2.6. Atmospheric pressure of the approaching flow is 40 kPa (corresponding to an altitude of about 56,500-m). For the conditions given, complete the following: Sketch the flow about the airfoil (show the shock waves, expansion fans, and slip-line) Compute the drag per unit span, D'. Compute the lift per unit span, L'. Determine the pressure and flow direction immediately downstream of the airfoil (just beyond the trailing edge). What is the velocity on each side of the slip-line?

Explanation / Answer

i will solve this in Ansys but need more than 30 min can u increase the time please.

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