Abstract:

The Menter’s local correlation-based transition model is investigated for numerical simulations of hypersonic boundary layer flows in this paper. By modifying pressure gradient parameter in the transition model and turbulent Prandtl number, the low speed transition model is corrected and applied to simulate hypersonic transition flows. The improved model is validated in several cases of hypersonic sharp cone flows under various conditions, involving different wall temperature, free stream turbulence intensity and pressure gradient in stream direction. The computational results are compared with wind tunnel experimental data relating to surface temperature, recover factor and heat transfer distribution. For all test cases, the onset and length of transition region are well predicted, and good agreements with measured data are observed. These results demonstrate that the improved model has potential as a predictive tool for hypersonic boundary layer transition flow.

Key words: Hypersonic flow, Transition model, Numerical simulation, Sharp cone