给定下游边界的超声速流场逆向求解方法  

An Inverse Method for Supersonic Flowfield with Given Downstream Boundary

作　　者：韩伟强[1] 朱呈祥[1] 尤延铖[1] 李怡庆 

机构地区：[1]厦门大学航空航天学院,福建厦门361005

出　　处：《推进技术》2016年第4期624-631,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金(51276151;91441128);国防基础科研(B1420133058);中央高校基本科研业务费(20720140540)

摘　　要：为了实现超声速流场出口参数的可控设计,借鉴特征线方法在古尔赛特与柯西问题两类边值条件中的应用,提出了一种根据下游边界条件求解其依赖域的逆柯西问题求解方法,并在此基础上发展了一种均匀来流条件下的超声速流场逆向求解方法。对轴对称内收缩流场、二维平面流场、轴对称外锥流场三个典型算例校核表明,逆向求解方法得到的计算结果与正向特征线方法一致,由此验证了该逆向求解方法的可行性,并有效拓展了超声速流场的设计思路。For the controllable design of exit parameters in supersonic flowfield, a new method of solving the inverse Cauehy problem, referring to the Method of Characteristics applied in the Goursat and Cauchy prob- lems, is proposed to calculate the domain of dependence according to known downstream condition. On this ba- sis, an inverse method for supersonic flowfield with the uniform flow condition is further developed. The valida- tion of three typical cases （axisymmetric internal compression flowfield, two-dimensional planar flowfield and external conical flowfield） shows that results obtained by the inverse method agree well with those obtained by forward MOC, which verifies the feasibility of the inverse method and expands the thought of supersonic flow- field design effectively.

关 键 词：特征线法 超声速流场 下游边界 逆向求解 

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]