Copyright © A. Filippone (1997-2005). All Rights Reserved.

Viscous-Inviscid Interaction

Airfoil Flow

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.

Angle of attack = 10.3

Figure 1: = 10.3 deg.

Angle of attack = 12.3

Figure 2: = 12.3 deg.

Angle of attack = 13.3

Figure 3: = 13.3 deg.

Helicopter Rotor Flow


  • Filippone A. Interaction of Potential Flow Model with the Navier-Stokes Equations for Rotor Aerodynamics, Ph.D. thesis, Rep. AFM-95-07, Tech. Univ. Denmark, Nov. 1995 (ISSN-0590-8809).
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Copyright © A. Filippone (1997-2005). All Rights Reserved.