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If an airfoil is designed to provide lift curve slope as 7.8, then find airfoil efficiency. The actual lift curve slope of the airfoil is 7.4.

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If an airfoil is designed to provide lift curve slope as 7.8, then find airfoil efficiency. The actual lift curve slope of the airfoil is 7.4.

(a) 94.87%

(b) 45%

(c) 15.6%

(d) 98.7%

The question was posed to me by my college director while I was bunking the class.

My question is taken from Aerodynamics topic in portion Aerodynamics of Aircraft Design

1 Answer

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The correct answer is (a) 94.87%

Explanation: Airfoil efficiency = Actual lift curve slope / theoretical or designed lift curve slope

= 7.4/7.8 = 0.9487 = 94.87%.

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