Question: 3. Compute the lift and drag coefficients for the triangular airfoil shown below when Mg = 2.0, o0 = 30, t/c =0.2, and xy/c =

3. Compute the lift and drag coefficients for the triangular airfoil shown below when Mg = 2.0, o0 = 30, t/c =0.2, and xy/c = 0.55. Use the exact values of pressure behind shock waves and expansion fans (i.e. do not use the small disturbance approximation). c

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