基于射流的宽速域定几何进气道流场控制方法研究  

Research on Method Based on Injection of Flow Field Control for a Wide Range of Fixed-geometry Inlet

作　　者：高明[1,2] 刘愿[1,2] 李雪飞 Gao Ming;Liu Yuan;Li Xuefei(Key Laboratory of Hypersonic Aerodynamic Force and Heat Technology,AVIC Aerodynamics Research Institute,Shenyang 110034,China;Aeronautical Science and Technology Key Lab for High Speed and High Reynolds Number Aerodynamic Force Research,AVIC Aerodynamics Research Institute,Shenyang 110034,China)

机构地区：[1]中国航空工业空气动力研究院高超声速气动力/热技术重点实验室,辽宁沈阳110034 [2]中国航空工业空气动力研究院高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《气动研究与试验》2024年第5期98-109,共12页Aerodynamic Research & Experiment

摘　　要：为满足吸气式高马赫数飞行器推进系统宽泛的工作包线要求,进气道设计时必须兼顾压缩效率和起动性能,然而设计点低于巡航马赫数的进气道往往存在压缩效率不足的问题。针对该问题,本文采用基于射流的流场控制方法,对定几何进气道的宽速域气动性能开展数值模拟研究,获得射流对进气道性能的影响规律。结果表明,针对Ma2.0~4.0的自由来流条件,当射流施加位置位于喉道下游适当距离处时,进气道喉道处以及扩张段监测面的总压恢复性能较优;在进气道喉道附近施加射流时,采用与来流夹角较大的射流角度效果较好,仅需很小的射流压力即可达到缩小气动喉道的目的。In order to meet the wide working envelope requirements of the propulsion system of the air breathing-high Mach number aircraft,the inlet design schemes must consider both the efficiency of compression and the starting performance,but the inlet which is designed by Mach number lower than the cruise Mach number will have the problem of insufficient compression efficiency.In order to solve this problem,the method based on injection of flow field control is used to simulate the aerodynamic performance of fixed-geometry inlet in wide velocity range.The results show that for the free flow condition of Ma 2.0~4.0,when the injection is applied at a proper distance of the throat,the total pressure recovery performance of the inlet throat and the monitoring surface of the expansion section is better.When the injection is applied near the inlet throat,the effect is better.When the angle between the injection and the incoming flow is larger,the low pressure value is enough to accomplish purpose of reducing the aerodynamic throat.

关 键 词：定几何进气道 射流 流场控制 数值模拟 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]