马赫数4.0颌下等熵混合压缩进气道技术研究  

An Investigation on Ma4.0 Chin Inlet with Isentropic Mixed-compression

作　　者：孟宇鹏[1] 朱守梅[1] 李宏东[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2014年第6期69-74,102,共7页Tactical Missile Technology

摘　　要：对一种设计马赫数4.0的等熵混合压缩颌下进气道进行了研究,采用计算流体力学和风洞试验两种手段,得到了进气道性能特性以及出口流场特性随攻角、侧滑角变化的规律。研究表明:相同设计马赫数下等熵压缩颌下进气道性能高于三锥压缩颌下进气道的性能;等熵压缩进气道在较小攻角下达到性能极值,随着攻角增大压缩效率和流量系数均会降低,随着侧滑角增大,性能降低;进气道出口流场不均匀度随着攻角的增大逐渐增大,流场畸变度不断增大;等熵压缩颌下进气道对攻角的变化比较敏感,适于以一定速度范围长时间巡航状态的导弹。An investigation of chin inlet with isentropic mixed-compression was performed by method of CFD and wind tunnel test. The performance variation curves versus the angle of incidence and of yaw was obtained. The results showed that the performance of chin inlet with isentropic mixed-compression was better than the sameone with tri-cone compression in equal Mach number range,the isentropic inlet have a maximum value performance in small angle of incidence. The total pressure recovery coefficient and mass flow ratio was reduced with the increasing of angle of incidence and angle of yaw. The unevenness of outlet flow field changed worse with the increasing of angle of incidence. The inlet distortion was increased with the increasing of angle of incidence. The chin inlet with isentropic compression was sensitived with variation of angles of incidence. This kinds of inlets was used for the cruising missile.

关 键 词：颌下式进气道 等熵压缩 计算流体动力学 风洞试验 

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]