Heat Transfer Predictions of Hypersonic Transitional Flows
Final rept. 1 Oct 1989-31 0ct 1990,
APPLIED AND THEORETICAL MECHANICS INC OAKLAND CA
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A numerical model to solve transition process observed in hypersonic flows over cones has been developed. Low Reynolds number two-equation turbulence models were employed with a production term modification PTM technique. The approach determined the extent of the transition zone. The onset of transition was imposed using experimental measurements when available. when not available, the onset of transition was determined by a stability criterion which is related to the Bushnell-Reshotko transition criterion. The PTM technique was incorporated into a NASA-Ames implicit Reynolds averaged Navier Stokes solver, the TURF code, and tested for transitional hypersonic flows over flat plates. The model parameters were tuned as a function of free stream Mach number. The PTM technique was also tested for transitional hypersonic flows over sharp cones and blunt cones for a variety of flow conditions. Comparisons of computed heat transfer with experimental measurements are shown to be good.
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