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 boundary layer transition has an important impact on the aerodynamic and thermal properties of the hypersonic vehicle.According to the Favré average Navier-Stokes equations, The numerical results are compared with the available experimental results. The results show that increasing the unit Reynolds number can lead to the early turnaround, and the angle of attack effect can delay the windward transition and advance the leeward transition.