基于求解三维Navier Stokes方程 ,首先数值预估了高超声速三维流动的边界层特性 ;采用已有的高超声速三维边界层转捩准则 ,即在转捩位置Reθ/Me=常数 ,以及通过修正由ONERA提出的代数转捩模型 ,建立了预估三维边界层转捩的半经验数值技术并应用于三维Navier Stokes方程的求解。利用HALIS模型及相关的实验数据 ,首次进行了在M∞ =6时不同雷诺数及迎角的验证试验。预估结果表明 :在不考虑边界层横向流动的影响下 ,预估结果与实验相当吻合 ;同时从工程应用的角度来说 ,由于其较少的计算工作量和易于在Navier Stokes程序中实现 ,本文所提出的数值预估技术具有良好的应用前景 Based on solving the Navier-Stokes equation, the boundary layer properties of hypersonic three-dimensional flow are first predicted numerically. The existing hypersonic three-dimensional boundary layer transition criterion (Reθ / Me = constant at the transition position) The proposed algebraic transition model was used to establish the semi-empirical numerical technique for predicting the transition of three-dimensional boundary layer. The semi-empirical numerical method was applied to the three-dimensional Navier Stokes equations. Using HALIS model and related experimental data, the validation experiments of different Reynolds numbers and angles of attack at M∞ = 6 were first carried out. The predicted results show that the predicted results are in good agreement with the experimental results without considering the lateral flow at the boundary layer. Meanwhile, from the perspective of engineering application, due to its low computational load and easy implementation in the Navier Stokes procedure, The numerical estimation technique proposed in this paper has a good application prospect