二元弯曲压缩进气道变攻角起动试验  

Variable angle of attack start experiment of 2D curved compression inlet

作　　者：朱伟 华正旭[2] 王霄 张堃元 梁剑寒[1] 王俊伟[2] ZHU Wei;HUA Zhengxu;WANG Xiao;ZHANG Kunyuan;LIANG Jianhan;WANG Junwei(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Shenyang Aircraft Design and Research Institute,Aviation Industry Corporation of China Limited,Shenyang 110035,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]中国航空工业集团有限公司沈阳飞机设计研究所,沈阳110035 [3]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2020年第5期992-999,共8页Journal of Aerospace Power

摘　　要：开展了内外压缩型面可控的弯曲压缩进气道反设计方法研究,并针对设计的二元弯曲压缩进气道进行了不同马赫数下变攻角起动数值仿真及试验研究,获得了进气道起动攻角迟滞环,仿真与试验得到的不起动/自起动攻角、出口流场以及压力分布吻合良好,同时试验结果也表明设计的弯曲压缩进气道具有较高的综合气动特性,设计点Ma=4、α=3°抗反压能力70倍来流压力以上,总压恢复系数在0.5以上。The reverse design method of curved compression inlet with controllable internal and external compression surfaces was studied,the numerical simulation and experimental study of the designed 2 D curved compression inlet starting with varying angle of attack at different Mach numbers were carried out,and the hysteresis loop of the inlet starting angle of attack was obtained.Simulation and experiment indicated that unstarting/self-starting angle of attack,the outflow field and pressure distribution coincided well,and the experiment results also showed that curved compression inlet had high comprehensive aerodynamic characteristics;at design points Ma=4,α=3°back pressure resistance ability was more than 70 times of inflow pressure,total pressure recovery coefficient was above 0.5.

关 键 词：弯曲压缩 进气道起动 反设计 风洞试验 迟滞现象 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]