双下侧二元混压式进气道不起动-再起动特性分析

摘要

针对某典型固冲发动机用双下侧布局二元混压式进气道的不起动-再起动特性,开展了高速风洞试验和弹体/进气道一体化数值仿真研究.研究结果表明,进气道极限反压与来流总压、喉道总压恢复系数和流量系数相关;进气道入口前气流总压是决定进气道再起动反压的主要因素;在侧滑情况下,背风侧进气道抗反压能力强于迎风侧,且两侧进气道再起动不同步%Supersonic wind tunnel experiment and integrated simulation of missile/inlet were carried on,in order to investigate the unstart and restart characteristics of the solid ducted rocket mixed compression inlet with the configuration of 90°on both down side.The results showed that the utmost back pressure depends on the total pressure of the incoming flow,the total pressure recovery and the mass flow coefficient.The incoming flow total pressure affected the back pressure of the inlets restart characteristic directly.The back pressure that the lee-side inlet could resist was higher than that of the windward side inlet,and the restart of the two-side inlets was inconsistent.