马赫数范围为0~4混合并联二元弯曲压缩进气道设计及试验研究  

Design and experimental research of Mach number range 0—42D mixed parallel-type curved compression inlet

作　　者：朱伟 王霄[1,2] 华正旭 张堃元[3] 梁剑寒 王俊伟[2] ZHU Wei;WANG Xiao;HUA Zhengxu;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》2023年第9期2271-2278,共8页Journal of Aerospace Power

摘　　要：采用内外压缩型面可控的弯曲压缩进气道反设计方法,设计了一种新型混合并联式二元弯曲压缩进气道,重点针对进气道模态转换过程及冲压单独工作条件下进行了数值仿真及试验研究,获得了进气道宽速域性能,结果也表明新型混合并联式弯曲压缩进气道具有较高的综合气动特性,冲压工作状态马赫数为4、攻角为3°时总压恢复0.5以上,马赫数为3、攻角为3°时总压恢复0.75以上,涡轮工作状态马赫数为2、攻角为3°时总压恢复0.88以上,综合畸变指数小于5%,满足宽速域进发匹配需求。Based on the internal and external compression surface controllable curved compression inlet reverse design method,a mixed parallel-type curved compression inlet was designed,numerical simulation and experiment research were conducted focusing on inlet model transition process and ramjet work alone,and wide speed performance of inlet was obtained.The result showed that,the new type parallel curved compression inlet had high comprehensive aerodynamic characteristics,at ramjet work alone state Mach number 4、Angle of attack 3°total pressure recovery coefficient was above 0.5,at Mach number 3、Angle of attack 3°total pressure recovery coefficient was above 0.75,at turbine work state Mach number 2、Angle of attack 3°total pressure recovery coefficient was above 0.88,composite distortion factor was under 5%,meeting the matching requirements of wide speed domain.

关 键 词：弯曲压缩 反设计 风洞试验 混合并联 涡轮基组合循环 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]