Investigation of turbulence models with compressibility corrections for hypersonic boundary flows

Abstract

The applications of pressure work, pressure-dilatation, and dilatation-dissipation (Sarkar, Zeman, and Wilcox) models to hypersonic boundary flows are investigated. The flat plate boundary layer flows of Mach number 5-11 and shock wave/ boundary layer interactions of compression corners are simulated numerically. For the flat plate boundary layer flows, original turbulence models overestimate the heat flux with Mach number high up to 10, and compressibility corrections applied to turbulence models lead to a decrease in friction coefficients and heating rates. The pressure work and pressure-dilatation models yield the better results. Among the three dilatation-dissipation models, Sarkar and Wilcox corrections present larger deviations from the experiment measurement, while Zeman correction can achieve acceptable results. For hypersonic compression corner flows, due to the evident increase of turbulence Mach number in separation zone, compressibility corrections make the separation areas larger, thus cannot improve the accuracy of calculated results. It is unreasonable that compressibility corrections take effect in separation zone. Density-corrected model by Catris and Aupoix is suitable for shock wave/boundary layer interaction flows which can improve the simulation accuracy of the peak heating and have a little influence on separation zone.

Coupling Simulation of Thermal Response to Exhaust Gas at External Nozzle

“…The Mach number of the inflows is so high that the effect of compressibility upon turbulence must be considered in this calculation target. Therefore, the compressibility correction proposed by Tang and Gao [25] is added to the turbulence calculation. The surface temperature and heat flux are measured during the experiment.…”