Aerospace Engineering > GATE 2013 > Thin Airfoil Theory
Circulation theory of lift is assumed for a thin
symmetric airfoil at an angle of attack α. Free stream velocity is U.
If the circulation at the quarter chord (c/4) of the airfoil is Γ1 the normal velocity is zero at
If the circulation at the quarter chord (c/4) of the airfoil is Γ1 the normal velocity is zero at
Correct : b
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