Discussion
Which is the correct relationship for the section lift coefficient in thin airfoil theory?
Answer: B
Correct answer: It is proportional to the angle measured from the zero-lift angle
Thin airfoil theory gives \( c_l = 2\pi(\alpha - \alpha_{L=0}) \) with the angle in radians. Camber enters only through the zero-lift angle, so it shifts the lift curve sideways without changing its slope - which is the theory’s most useful single result and the reason all thin sections share a slope of about 0.11 per degree.
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