23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-2.5.1

A CFD APPROACH TOWARDS MODELING BLADE/VORTEX IMPINGEMENT EFFECTSAND BUFFETING OVER AIRFOILS

M. Mamou, M. Khalid
Institute for Aerospace Research, National Research Council, Canada

Keywords: airfoil-vortex-interaction, shock wave oscillation, viscous separation

Unsteady flows resulting from airfoil-vortex-interaction (AVI) and a shockwave-boundary-layer-interaction (SBLI) are studied numerically using the Reynolds averaged Navier-Stokes equations. For the AVI problem, two NACA0012 airfoils are used in tandem. The lead airfoil is used to generate a vortex and the aft one to intersept the vortex and undergoes the AVI process. The interaction of the vortex with the aft airfoil has notable effects upon its aerodynamic characteristics. For the SBLI problem, unsteady separated unsteady flows past an 18% thick circular-arc-airfoil and the BGK No. 1 airfoil are studied. The results demonstrated that the unsteady behavior of the flow is sensitive to the turbulence models.

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