A semi convex airfoil is immersed in a uniform supersonic flow at Mach M_∞=2.0 with an...

A semi convex airfoil is immersed in a uniform supersonic flow at Mach M_∞=2.0 with an incidence angle α=3 degrees, as is shown in figure : The upper surface has the following equation with respect to the body system of reference: y=-(4x^2)/c^2 +4hx/c Where h/c=0.02 The lower surface is flat. Determine: (a) The airfoil lift coefficient CL. (b) The airfoil drag coefficient Cd

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genius_generous answered 2 years ago

Sample practice Ch. 6B – Silimar to Homework 6-15 Consider a horizontal supersonic flow a Mach...

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