Question

Consider a diamond-‐wedge airfoil in high speed flow. The half
angle of the airfoil is ? = 6^{o}

Consider angle of attack values, ? = 6^{o}

Consider free stream Mach numbers, ? = 10

Using linearized supersonic theory and Newtonian theory for hypersonic flow, calculate the lift and drag coefficient for the airfoil for the given condition.

Validate your results using the shock-expansion theory for case.

Answer #1

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