高超进气道自适应泄压槽的设计参数分析

采用自适应泄压控制技术解决宽范围定几何高超进气道低马赫数下自起动问题,利用数值仿真对一种采用自适应泄压控制的高性能二元高超进气道单个自适应泄压槽的位置、角度、有效流通面积等主要设计参数对泄漏量以及进气道总体性能的影响规律开展了研究.结果表明:泄压槽参数变化对基准进气道总体性能影响较小,总压恢复系数在2％范围内变化.位于唇口激波反射点下游的槽的泄漏量较大且随开槽角度的增加而减小,随有效流通面积的增加成线性增加；相同条件下,自适应泄压槽的泄漏量只有常规顺向放气槽的50％；随来流马赫数升高,自适应泄压槽的漏气量明显减小,高马赫数下接近气动自封闭状态.

Parameters analysis of adaptive pressure relief slot in hypersonic inlet

In order to improve self-starting performance of the fixed-geometry inlet at low Mach number,a technology of self-adaptive pressure relief slot was proposed.The law about the location,direction and effective area of single adapted pressure relief slot was studied with a high performance two-dimensional hypersonic inlet utilizing the technology of numerical simulation.The result shows that:the slot has little influence on the model inlet,and the total pressure recovery ranges around 2%;the slot located downstream the cowl shock wave has large outgassing rate,which will increase as the angle descends and the effective area ascends.The outgassing rate of the adapted pressure relief slot is just 50% compared with normal slot under the same condition.It will drop as the Mach number increases,approaching self-close state at high Mach number condition.