高超声速尖锥边界层转捩数值模拟

Hypersonic boundary layer transition prediction based on laminar fluctuation energy transport equation

边界层转捩对高超声速飞行器气动力和热产生重要影响.通过联立求解Favré平均层流脉动能方程与Favré平均Navier-Stokes方程,开展了高马赫数条件下尖锥边界层转捩位置的数值预测研究.将数值计算结果与可用的实验结果进行对比,结果表明增大单位Reynolds数可使转捩提前发生,攻角效应可使迎风面转捩延迟,背风面转捩提前.

The transition of boundary layer flows has crucial effects on aerodynamic and heat performances of hypersonic vehicles.The fluctuation energy transport equation based on Favré average was solved in conjunction with the Favré averaged Navier-Stokes equations to predict the onset of the boundary layer transition.By comparing with the available experimental data,numerical results demonstrate that larger unit Reynolds number produces earlier transition,and the angle of attack delays transition on the windward surface,while promotes it on the leeward surface.