摘要
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 。
Based on solution of the 3D Navier Stokes solver, the characteristic boundary layerproperties for three dimensional hypersonic flow have been numerically evaluated. By using an existing transition criteria for hypersonic boundary layer, the Re θ/M e =constant at transition, and adding the algebraic transition model originally developed by ONERA/CERT,a semi empirical numerical technique to predict the transition effects on the heating of reentry vehicles has been established and implemented into the 3D Navier Stockes solver.First validation tests at M ∞ =6 have been carried out using the HALIS configuration and correlated with available experimental data. The predicted results show that the heating distributions are in good agreement with those given by experiments as far as boundary layer crossflow effects are negligible. Within the frame of engineering methods, the present technique appears very promising due to its low computational effort and easy implementation into Navier Stokes codes.
出处
《空气动力学学报》
CSCD
北大核心
2000年第4期490-494,共5页
Acta Aerodynamica Sinica
