高超声速飞行器进气道等离子体虚拟前沿优化设计

为研究等离子体虚拟前沿在高超声速飞行器前体/发动机一体化设计中的应用,首先设计了二波系前体,然后分析了虚拟前沿对前体流场结构的影响,最后通过比较虚拟前沿结构参数及位置对总压恢复系数、流量系数等参数的改善效果,优化得出了最佳虚拟前沿。结果表明,有虚拟前沿控制前体激波时,总压恢复系数及流量系数都会增大,但压缩比不一定会增大;虚拟前沿的位置对各参数的影响很大,且存在一个最佳位置使得前体性能最好;随着虚拟前沿长度的增大,总压恢复系数和流量系数逐渐增大,压缩比逐渐减小。

Optimization Design of Plasma Virtual Cowl in Scramjet Inlet

First,an inlet of wave-rider formed by two step wedge was design to investigate the application of plasma virtual cowl on the airframe/scramjet integration design of wave-rider.Then the effect of virtual cowl to the flow field was investigated.Finally,an optimization virtual cowl has been got based on the effects of its position and parameters to the total pressure recovery coefficient and flow coefficient of the scramjet inlet.The results show that,total pressure recovery coefficient and flow coefficient will be improved for the application of virtual cowl,but the compression rate can not be always.As the big influence of virtual cowl position to the parameters of the scramjet inlet,there is an optimization position to the virtual cowl.As the length of virtual cowl increase,total pressure recovery coefficient and flow coefficient will increase,but compression rate will decrease.