GATE 2016 Aerospace Engineering: Thin Airfoil Theory - dCm/dα at Half Chord

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Aerospace Engineering > GATE 2016 > Thin Airfoil Theory

The rate of change of moment coefficient with respect to the angle of attack, dC_m/dα , at half chord point of a thin airfoil, as per approximations from the thin airfoil theory is

A

π/4 radian^-1

B

π/2 radian^-1

C

π radian^-1

D

2π radian

Correct : b

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