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LoginThe Kutta Condition according to the thin airfoil theory is_____
(a) γ(c)=0
(b) γ(x)=0
(c) γ(ξ )=0
(d) \(\frac {dz}{dx}\)=0
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I'm obligated to ask this question of The Symmetric Airfoil in division Incompressible Flow over Airfoils of Aerodynamics
Aerodynamics Incompressible Flow over Airfoils in Aerodynamics 3 years ago
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.
Posted on 02 Dec 2021, this text provides information on Aerodynamics related to Incompressible Flow over Airfoils in Aerodynamics. Please note that while accuracy is prioritized, the data presented might not be entirely correct or up-to-date. This information is offered for general knowledge and informational purposes only, and should not be considered as a substitute for professional advice.
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