A Computational Investigation of Flow Through an Axisymmetric Supersonic Inlet

Abstract

A Reynolds-averaged Navier Stokes (RANS) solver is used to study the flow through an axisymmetric, supersonic inlet at a freestream Mach number of 1.974. Axisymmetric and three dimensional calculations are performed. The effects of struts in the flowfield and shock wave boundary layer interaction on total pressure recovery and distortion are studied. Three dimensional calculations are performed at angles of attack (AOA) of 0, 2, and -2. The effect of streamwise vorticity generated in the wake of the struts on pressure recovery and total pressure distortion is studied. Comparisons are made to experimental results from tests done at the NASA Glenn Research Center (GRC). It is shown that the current RANS methodology overpredicts total pressure recovery by 0.7%, and the threedimensional calculations overpredict total pressure recovery by less than 0.5% for most cases. The axisymmetric calculations predict radial total pressure distributions with reasonable accuarcy, and the three-dimensional calculations predict radial and circumferential total pressure distributions with reasonable accuracy.