定几何混压式轴对称超声速进气道设计及性能计算  

Design and Performance Calculation of the Mixed-Compression Fixed-Geometry Axisymmetric Supersonic Inlets

作　　者：陈兵[1] 徐旭[1] 王元光[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2005年第3期373-379,共7页Journal of Aerospace Power

摘　　要：给出了定几何混压式轴对称超声速进气道型面设计及性能计算方法,进行了算例计算。对亚临界状态下脱体激波的计算进行了研究,给出了进气道临界状态性能参数随飞行马赫数和高度的改变而变化的曲线。分析了进-发匹配过程,以及进气道的自调节能力。计算得到了基于进气道性能最优,即进气道工作在临界状态条件下,碳氢燃料冲压发动机的供油规律,为进气道大范围寻优设计打下了基础。Geometric design method of mixed-compression fixed-geometry axisymmetric supersonic ramjet inlet was presented. Performance calculations of inlet under on-or off-design conditions were carried out with special attention to the detached bow shock calculation during subcritical operations. The influence of flight Mach number and altitude on inlet critical condition performance has been evaluated. The inlet-engine matching mechanism was investigated, and the fuel supply characteristics were obtained to maintain the optimum inlet performance. The successful study provides a good reference to the design of ramjet supersonic inlets.

关 键 词：航空、航天推进系统 超声速进气道 性能计算 脱体激波 进一发匹配 供油特性 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]