高速底部流动含有膨胀波、自由剪切层、分离涡、激波等复杂现象，气动热环境精确计算是具有挑战和丞待解决的技术难题。飞行器底部热环境相对身部低很多，一直以来未得到重视，理论研究远远落后于实践。随着机动飞行器的发展及深空探测飞行器有效载荷的需求，对飞行器底部热防护结构质量限制越来越高，飞行器尾部热环境裕度设计已经不能满足工程设计需要，急需改进计算方法。近年来兴起的RANS/LES混合算法在底部流场计算方面已经取得了突破性的进展，本项研究将围绕底部流动加热机理和计算方法，研究影响尾部复杂流动热环境计算的主要因素，将RANS/LES混合算法扩展至尾部热环境计算，发展RANS/LES混合算法，以适应尾部热环境计算的需求，同时建立数值与工程相结合的新方法，为解决尾部热环境问题开辟新的途径，研究结论将有助于对高速底部热环境的理解。

Accurate computation of high speed base flow aerothermal environment is a challenge problem, because expansion Fan, free shear layer, retachment shock, seperation bublle are included in base flow. Theories and methods in base flow is lag practice because of low heat transfer and not attached importance to it by researchers. By the development of maneuver vehicles and capsuls,the safe design of base aerothermal environment can't satisfy the engineering design because the room and weight is limited. RANS/LES hybrid method developed rencent year made it is possible to resolve the aerothermal environment of base flow. This research will study the heating mechanism , computation methods and the main effects. RANS/LES hybrid method is developed to compute aerothermal environment in base flow. and a new method which combine the numerical and engineer method will be established. The reserch will find new approach to solve aerothermal environment of base flow and will promote the understanding of aerothermal environment in base flow.