Compute lift produced by the airfoil

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Reference no: EM13709563

The figure on the right shows an approximated pressure distribution on an airfoil and the direction of incoming flow. Alpha is 10 degrees, the pressure distribution on the top is 3n/m and on the bottom is 1n/m. The chord Length is 1 meter.

a. Compute Lift produced by the airfoil

b. Compute Drag produced by the airfoil

c. Compute Lift Coefficient from (a) and Drag Coefficient from (b) if the airspeed is 0.5 m/sec at sea level density

Reference no: EM13709563

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