Menter转捩模型在高超声速流动模拟中的改进及验证

Improvement and Validation of Menter's Transition Model for Hypersonic Flow Simulation

通过压力梯度参数和湍流普朗特数的修正,对Menter等构造的低速经验关系式转捩模型进行了改进,将基于局部信息的Menter转捩模型用于高超声速流动转捩数值模拟。在多个高超声速尖锥转捩流动模拟中,对改进后模型的可靠性进行了检验,算例考核了不同壁面温度、来流湍流度、流向压力梯度等多种流动条件。结果表明,数值计算和风洞试验的壁面温度、温度恢复因子和热流等符合得较好,修正后模型较好地模拟了转捩起始位置和转捩区长度,在高超声速边界层转捩预测中具有一定潜力。

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.