Aerospace Engineering > GATE 2015 > Thin Airfoil Theory
Consider a NACA 0012 aerofoil of chord c in a freestream with velocity V∞ at a non-zero positive angle of attack α. The average time-of-flight for a particle to move from the leading edge to the trailing edge on the suction and pressure sides are t1 and t2, respectively. Thin aerofoil theory yields the velocity perturbation to the freestream as -Vx(1+cos θ)α/sin θ on the suction side and as Vx(1+cos θ)α/sin θ on the pressure side, where θ corresponds to the chordwise position, x=c/2(1-cos θ). Then t2-t1 is
Correct : a
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