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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。
In order to study the application of plasma virtual front in the design of hypersonic vehicle precursors / engines, a two-wave system precursor is designed. Then the influence of virtual front on the precursor flow field structure is analyzed. Finally, by comparing the virtual front structure Parameters and position of the total pressure recovery coefficient, flow coefficient and other parameters to improve the effect, optimize the best virtual front. The results show that the total pressure recovery coefficient and the flow coefficient will increase when the precursor is controlled by the virtual frontier, but the compression ratio will not necessarily increase. The location of the virtual front has a great influence on each parameter, and there is a best With the increase of the length of the virtual front, the total pressure recovery factor and the flow coefficient gradually increase, and the compression ratio decreases gradually.