Violet3880 Violet3880

13-12-2022
Engineering

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Study problem about Supersonic Thin-Airfoil Theory, you do not need to submit)A diamond shape airfoil with a thickness ratio (t/c) of 0.08 is placed in supersonic flow with a free-stream Mach number of 2.0. The angle of attack of the airfoil is zero, (a) Use the supersonic thin-airfoil theory to calculate the drag coefficient (C_D) of the airfoil. (b) Calculate the drag coefficient of the same airfoil at the same Mach number using the shock-expansion theory, which is going to give you the exact result for supersonic flow. Compare your result (calculate the percent difference) to the drag value obtained in part (a).

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