Question: A thin circular-arc airfoil is shown in Fig. P9.156. The leading edge is parallel to the free stream. Using linearized (small turning- angle) supersonic-flow theory,

A thin circular-arc airfoil is shown in Fig. P9.156. The leading edge is parallel to the free stream. Using linearized (small turning- angle) supersonic-flow theory, derive a formula for the lift and drag coefficient for this orientation, and compare with Ackeret-theory results for an angle of attack α = tan€“1(h/L).

A thin circular-arc airfoil is shown in Fig

Ma LE Circular-arc foil TE Ap upper Ap lower

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