MAE 150B - 04A - Incompressible Flow over Airfoils

# MAE 150B - 04A - Incompressible Flow over Airfoils - MAE...

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MAE 150B - Chap 4 part A Incompressible Flow Over Airfoils

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Cylinder flow provides basic knowledge on the incompressible flow over airfoils
Kutta Condition Using conformal mapping, flow over a circular cylinder can be transformed to flow over an airfoil There are two stagnation points: one near leading edge (LE) and the other one locates close at the tailing edge (TE) What happens if flow has an angle of attack

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Kutta Condition (Cont.) Without a vortex, the TE stagnation will not be at the TE There will be a sharp turn of flow at TE The radius of curvature is “0” at TE infinite (or at least very large) acceleration at TE Possible in inviscid flow but not in real life Viscous effects takes over
Kutta Condition (Cont.) The viscous effects will adjust the flow in such a manner that the sharp turning at TE is eliminated This is equivalent to add a vortex (circulation) to the flowfield At TE, the Bernoulli’s equation leads to same speed and same angle at TE

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## This note was uploaded on 10/09/2009 for the course MAE 150B taught by Professor D during the Spring '09 term at UCLA.

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MAE 150B - 04A - Incompressible Flow over Airfoils - MAE...

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