Numerical Investigation of a Blunt-Nosed Elliptical Cone at High Angle of Attack in Nonequilibrium Flow

†‡ * A computational fluid dynamics investigation was conducted on a blunt-nosed elliptical cone configuration. The purpose of the study was to investigate the advantages of high angle of attack reentry for a simple configuration representative of a flight vehicle. The geometry and test conditions were selected for comparison to experiments: a 2:1 blunt elliptic cone configuration at a Mach number of 14.5, Reynolds number based on length of 36000, and angles of attack ranging from of 0° to 60°. The calculations were carried out using the unstructured-grid, Reynolds-averaged Navier-Stokes code US3D, developed at the University of Minnesota. This code has frozen and non-equilibrium flow capabilities, but only non-equilibrium solutions were obtained in the present computational effort. The leeside flow structure was examined in detail, and grid resolution studies and comparison to the available experimental data for surface pressure and heat transfer were carried out.

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