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Engineering, 19.03.2021 01:00 marlesly87

A symmetrical airfoil of 2 m chord is used to produce a lift per unit span of 900 N/m when flying through sea level air at a speed of 60 m/s. Compute the sectional lift coefficient of the airfoil, from which you should then determine the angle of attack required (in degrees) to produce such a lift assuming TAT.

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