A fl at-plate airfoil with C = 1.2 m is to have a lift of30 kN/m when fl ying at 5000-m standard altitude withU∞= 641 m/s. Using Ackeret theory, estimate (a) the angleof attack and (b) the drag force in N/m.

A fl at-plate airfoil with C = 1.2 m is to have a lift of30 kN/m when fl ying at 5000-m standard altitude withU∞= 641 m/s. Using Ackeret theory, estimate (a) the angleof attack and (b) the drag force in N/m.

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Chapter5: Analysis Of Convection Heat Transfer

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Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

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Question

A fl at-plate airfoil with C = 1.2 m is to have a lift of
30 kN/m when fl ying at 5000-m standard altitude with
U_∞= 641 m/s. Using Ackeret theory, estimate (a) the angle
of attack and (b) the drag force in N/m.

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