高超声速边界层转捩和湍流计算问题  

Transition Prediction and Turbulence Computation of Hypersonic Boundary Layers

作　　者：周恒[1] 

机构地区：[1]天津大学力学系,天津300072

出　　处：《现代防御技术》2014年第4期1-8,54,共9页Modern Defence Technology

摘　　要：计算流体力学方法在飞行器的研制中正起着越来越大的作用。相比于实验受制于在地面无法完全实现真实飞行所遇到的条件,有其优势。但要做到准确估算各种气动载荷,如摩阻和热载荷,前提是能准确预测转捩位置和有湍流计算的能力。分析了国外流行的转捩预测方法及湍流计算模式中存在的问题。介绍了相应的改进方法。The method of computational fluid dynamics （CFD） plays a more and more important role in the research and development of flying vehicles.Compared with experiments that the real flying conditions can hardly be completely reproduced in ground test,CFD has obvious merit.However,for the accurate prediction of aerodynamic and aerothermal loading,such as the friction force and heat effect,a pre-condition is the capability of accurate prediction of the transition location and accurate computation of turbulent flows.The problems existing in the transition prediction method and turbulence models prevailing in countries abroad are analyzed,and the methods for their improvements are proposed.

关 键 词：高超声速 边界层转捩 湍流计算 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]