![]() Viscous-Inviscid InteractionAirfoil FlowBelow are shown some results of a viscous-inviscid interaction tecnique for airfoil flows. The airfoil is the ONERA-A at Re = 2.8 million, and angles of attack indicated in the figures. The inviscidmodel was a first order doublet potential; the viscous model was the Navier-Stokes equations in vorticity- streamfunction.
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Figure 3: Helicopter Rotor FlowReferences
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