多级压缩锥导乘波体设计与分析  

Design and Analysis of Multistage Compression Cone-Derived Waverider Configuration

作　　者：吕侦军 王江峰[1] 伍贻兆[1] 程克明[1] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016

出　　处：《宇航学报》2015年第5期518-523,共6页Journal of Astronautics

基　　金：江苏高校优势学科建设工程资助项目

摘　　要：提出了多级压缩锥导乘波体的设计方法,该方法应用吻切锥理论和零攻角圆锥绕流基准流场通过流线追踪生成具有多个压缩面的乘波体。对以吸气式冲压发动机为动力的高超声速飞行器,应用多级压缩乘波前体可充分发挥前体的预压缩作用,为进气道的正常工作提供所需的均匀流场。以二级压缩乘波体为例阐述了该设计方法,设计方法通过对二级压缩基准流场进行重构,使其符合Taylor-Maccoll流动模型以获得新的二级压缩基准流场。同时编写设计程序生成了一级、二级和三级压缩乘波体,通过数值模拟结果校验设计方法的正确性,并对其压缩性、升阻比、总压恢复系数等性能进行了对比分析。A new design method for multistage compressed waverider configuration is presented. According to the theories of conical flow field and osculating cone, a waverider configuration with multiple compressive ramps is obtained by tracing streamline method. For hypersonic vehicle powered by air-breathing scramjet, the multistage compressed waverider is used as the hypersonic vehicle＇ s forebody to make full use of pre-compression of the forebody and provide a uniform flow field for inlet＇ s normal work. Based on the assumed flight condition, the two-stage compressed waverider＇ s aerodynamic configuration is designed. The shape of shock wave is validated and the aerodynamic characteristics are analyzed by using numerical simulation to show the validation of multistage compressed waverider design method.

关 键 词：气动布局 高超声速 乘波体 多级压缩 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]