Below 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.
Figure 1: = 10.3 deg.
Figure 2: = 12.3 deg.
Figure 3: = 13.3 deg.
Helicopter Rotor Flow
Copyright © A. Filippone (1997-2005). All Rights Reserved.