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The Kutta Condition according to the thin airfoil theory is_____(a) γ(c)=0(b) γ(x)=0(c) γ(ξ )=0(d) \(\frac {dz}{dx}\)=0This question was addressed to me in a job interview.I'm obligated to ask this question of The Symmetric Airfoil in division Incompressible Flow over Airfoils of Aerodynamics

Answer»

Right choice is (a) γ(c)=0

The explanation is: The Kutta Condition says the flow leaves the trailing EDGE smoothly. The trailing edge is at CHORD length c for a thin airfoil which gives γ(c)=0. Also, γ(x)=0 or γ(ξ)=0 is not true for all x or ξ. \(\FRAC {dz}{dx}\)=0 is the definition of the symmetric airfoil, not Kutta condition.


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