摘要
提出了用相交楔锥流场构造乘波构型飞行器前体的方法。该方法利用无粘相交楔锥流场生成具有两个压缩面的乘波前体,不仅兼具楔型流场和锥型流场构造乘波体的优点,而且充分发挥了高超声速飞行器前体的预压缩作用,为进气道的正常工作提供了条件。同时用数值模拟的方法研究了不同前体压缩角度组合的预压缩效果,并在压缩角优化的基础上进行了前体/进气道的一体化设计。
A new method is provided to generate waverider configuration. In an intersectant wedge/cone flow field with two different wedge angles, a new kind of waverider is obtained through tracing streamline, which has two compressive ramps. This new waverider has not only the advantages of those generated from cone flowfield and wedge flowfield, but also excellent compressibility of forebody and nice quality of flow field. The latter is also very important for hypersonic vehicle. Furthermore, the optimal compressive angle combination is selected by numerical simulation and integrated design of forebody/inlet is performed in order to get maximum capture mass at the entry of the inlet. The numerical result shows that the waverider forebody can provide highly compressed and good qualified flow field for inlet and engine work.
出处
《工程力学》
EI
CSCD
北大核心
2003年第6期130-134,共5页
Engineering Mechanics
关键词
乘波体
相交楔锥
压缩性
一体化设计
waverider
intersectant wedge/cone
compressibility
integrated design
