Question

For α=5°, A0=1 and A1=-2 total circulation Γ for a thin cambered airfoil equals______

(a) 0

(b) 2πcV∞

(c) πcV∞

(d) 2.5πcV∞

The question was posed to me during an interview for a job.

Question is from The Cambered Airfoil in portion Incompressible Flow over Airfoils of Aerodynamics

Answer 1

Right choice is (a) 0

For explanation I would say: From the formula of total circulation Γ=cV∞(πA0+\(\frac {\pi }{2}\)A1) we get Γ=0 upon putting the values given in the question.