A computational investigation of flow through an axisymmetric supersonic inlet
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 and compared to experimental results, showing a good qualitative and quantitative agreement. 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 in the boundary layer is studied. A second axisymmetric supersonic inlet is studied at takeoff and cruise conditions. Takeoff calculations are performed at Mach numbers of 0 and 0.3 at sea level conditions. At Mach=0, cases are run with a 20 knot crosswind and with no crosswind. At Mach=0.3, cases are run at 0 degrees and 5 degrees AOA. At cruise conditions, the freestream Mach number is 1.7, and angles of attack of 0 degrees and 3 degrees are studied. The effect of flow separation and vorticity created by shock wave-boundary layer interaction and strut interactions are studied, as well as the inclusion of an annular bypass duct around the engine inlet.
Blaisdell, Purdue University.
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