Numerical solutions to the Reynolds-averaged Navier-Stokes equations are given for the flow about an elliptical body missile (3:1 ellipse) at a Mach number of 2.5 and a Reynolds number of 4.66 x 10 6 based on body length. At high angles of attack, the flow is dominated by large-scale free vortices that occur in the leeside flowfield due to crossflow boundary-layer separation. Emphasis is focused on the accurate prediction of the leeside vortical flow. Solutions are presented for both symmetric and asymmetric (body rolled 45 deg) configurations at 10 and 20 deg angles of attack. The computed results are compared with experimental surface pressure measurements and vaporscreen photographs. Excellent agreement is obtained in all cases.
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