内转式进气道/冯·卡门乘波体一体化设计方法  

Integrated design method of inward turning inlet/Von Karman waverider

作　　者：张文浩 柳军[1] 丁峰[1] ZHANG Wenhao;LIU Jun;DING Feng(Science and Technology on Scramjet Laboratory,College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院高超声速冲压发动机技术重点实验室,长沙410073

出　　处：《航空学报》2020年第3期188-199,共12页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11702322);国家重点研发计划(2019YFA0405202)。

摘　　要：应用特征线理论设计了内转式轴对称基准流场以及外压缩轴对称基准流场,利用激波交线、流线追踪方法等相关技术提出了一种头部进气式的高超声速飞行器内转式进气道/冯·卡门乘波体一体化设计方法,并对生成的一体化构型进行了数值模拟及分析,数值结果验证了该方法的正确性和有效性。该一体化设计方法基本保留了内转式进气道的优良特性,并以高升阻比乘波体为原型构建较高升阻比的一体化构型,从流场耦合的角度出发为减弱机体与进气道之间复杂的波系干扰,实现飞行器内外流的完全耦合进行了探索。The method of characteristics is applied to design the inward turning axisymmetric basic flow field and the external compressing axisymmetric basic flow field.An integrated design method of inward turning inlet/Von Karman waverider for hypersonic vehicle with head-intake is proposed based on the shock intersection line and streamline tracing.The integrated configuration is also presented and an analysis of the integrated configuration is carried out,verifying the correctness and the feasibility of the method.The excellent characteristics of the inward turning inlet is basically retained for using the integrated design method and the integrated configuration is constructed by using the waverider with a high lift-drag ratio as the prototype.From the view of flow field coupling,the paper intends to reduce the complex wave interference between the body and the inlet,realizing the complete coupling of the internal and external flow of the aircraft.

关 键 词：高超声速内转式进气道 基准流场 内外流耦合 一体化设计 流线追踪 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]