Parallel solution of low aspect ratio rectangular flat wings in compressible flow

Abstract

Two block parallel Navier Stokes solutions of an aspect ratio 1.0 flat plate with sharp edges are obtained at different Mach numbers and angles of attack. Reynolds numbers are of the order of 200,000-300,000. The flow field is dominated by vortices and separated flows. Two different grid configurations, the course and the fine grids, are applied in order to speed up the convergence. Total number of grid points is 700,000 in the fine grid. Baldwin Lomax Turbulence model with Degani Schiff and other modifications and an algebraic turbulence model for wakes are used. Pressures of the top surface are predicted well with the exception of the leading edge region. The predicted surface streamlines are in good agreement with the experiment. Periodic unsteady bubble formation is observed. Copyright © 2005 by the American Institute of Aeronautics and Astronautics, Inc.