23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-R29

SOLUTION OF AIRFOIL-FLAP CONFIGURATIONS BY USING CHIMERA GRID SYSTEM

E. Tarhan (1), E. Oktay (1), M. S. Kavsaoglu (2)
(1) ROKETSAN, Missile Industries, Inc., 06780 Ankara Turkey; (2) Middle East Technical University, Turkey

Keywords: euler, navier stokes, chimera

Overset grid Euler/Navier-Stokes solutions of airfoil-flap configurations are obtained. Beam-Warming scheme with finite differencing is used. The donor cell searching is done with the 'directional walking algorithm' and the localization criterion is done with the 'summation of areas' method. For the intergrid boundary points, 'bilinear interpolation technique' is used.

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