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.
A second identical airfoil is placed behind the first one at a distance of c/2 from the trailing edge of the first. The second airfoil has an unknown circulation Γ2 placed at its quarter chord. The normal velocity becomes zero at the same chord-wise locations of the respective airfoils as in the previous question. The values of Γ1 and Γ2 are respectively
A second identical airfoil is placed behind the first one at a distance of c/2 from the trailing edge of the first. The second airfoil has an unknown circulation Γ2 placed at its quarter chord. The normal velocity becomes zero at the same chord-wise locations of the respective airfoils as in the previous question. The values of Γ1 and Γ2 are respectively
Correct : a
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