Consider a flat-plate airfoil at an angle of attack of 6°. TheMach number is Ma∞ = 3.2 and the stream pressure p∞ isunspecified. Calculate the predicted lift and drag coefficientsby (a) shock-expansion theory and (b) Ackeret theory.

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A: Given data: Chord, C = 1.2 m Velocity , U∞ = 641 m/s Airfoil lift, F = 30 KN/m   Now from properties…

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A: Please go through the answer. This is the second time I'm answeringExplanation:

Q: Derive agenral expressionfind circulation and hte lift force for NACA 27014

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