Question: A flat plate airfoil with chord C = 1 . 2 m is to have a lift of 9 kN / m when flying at

A flat plate airfoil with chord C =1.2 m is to have a lift of 9 kN/m when flying at 5000-m standard altitude with U\infty =641 m/s. Using Ackeret theory, estimate (a) the angle of attack; and (b) the drag force in N/m.

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