Abstract
This paper deals with a numerical study of the base part of the supersonic flow past an aircraft model. The simulation was carried out using the software developed by the authors for calculating 3D turbulent flow of viscous compressible gas in the framework of the unsteady Reynolds averaged Navier–Stokes equations (URANS) with the Spalart–Allmaras (SA) and Menter’s SST turbulence models. Flight modes with M = 2.5 and angle of attack α = 0°, 3° were considered. A comparison is made of the effect of the choice of the turbulence model on the base flow.
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