Circulation theory of lift is assumed for a thin symmetric airfoil at an angle of attack $\alpha$. Free stream velocity is $U$.

If the circulation at the quarter chord $(c / 4)$ of the airfoil is $\Gamma_{1},$ the normal velocity is zero at
(A) $c / 4$
(B) $c / 2$
(C) $3 c / 4$
(D) all points on the chord

Question ID - 156212 | SaraNextGen Top Answer

Circulation theory of lift is assumed for a thin symmetric airfoil at an angle of attack $\alpha$. Free stream velocity is $U$.

If the circulation at the quarter chord $(c / 4)$ of the airfoil is $\Gamma_{1},$ the normal velocity is zero at
(A) $c / 4$
(B) $c / 2$
(C) $3 c / 4$
(D) all points on the chord