弹用“X”型倒置二元进气道方案与常规正置方案的气动性能对比  

Aerodynamic performance comparison of a two-dimensional inlet for missile in an inverted “X”-type layout with classical layout

作　　者：罗皓 金志光[1] 张堃元[1] LUO Hao;JIN Zhiguang;ZHANG Kunyuan(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院

出　　处：《航空动力学报》2019年第11期2366-2376,共11页Journal of Aerospace Power

摘　　要：为提高来流马赫数范围为2~4的"X"型进气系统大攻角下的稳定裕度,设计并研究了一种倒置二元进气道设计方案,并将其与正置方案进行了比较。结果表明:来流马赫数为2.3~3.5,攻角范围为0°~6°时,倒置布局设计方案总体性能较优,未出现明显激波/附面层干扰问题,能够满足设计要求。在采用相同的进气道设计方案时,倒置布局其迎风与背风进气道结尾激波位置及总体性能参数差异更小;0°攻角时倒置布局临界总压恢复系数与正置布局相当,4°攻角时倒置布局比正置布局高2%~3%,8°攻角时普遍高19%以上,且来流马赫数越高提升幅度越明显,8°攻角下倒置布局总流量系数较正置布局高6%左右。研究还发现,当来流马赫数较低时倒置布局总阻力低于正置布局,4°攻角时低1.7%;而来流马赫数较高时倒置布局总阻力高于正置布局,4°攻角时高2.0%。In order to raise the stability margin of"X"-type inlet system with incoming Mach number range from 2 to 4 at a high angle of attack,an inverted two-dimensional inlet was designed and compared with the classical inlet layout.Results indicate that the inverted inlet layout has better overall performance at incoming Mach number 2.3 to 3.5 with angle of attack from 0°to 6°.There is no obvious phenomenon of shock/boundary layer interactions,allowing to meet the design requirements.When the same inlet design scheme is adopted,the terminal shock location and overall performance parameters have little differences between windward and leeward inlets of the inverted layout.The critical total pressure recovery coefficient of the inverted layout is almost equal to classical layout when the angle of attack is 0°,2%-3% higher when the angle of attack is 4°and generally 19% higher when the angle of attack is 8°.The higher the incoming Mach number is,the more obvious the increase is.The total mass flow coefficient of the inverted layout is about 6% higher at angle of attack 8°.Moreover,the total drag force of inverted layout is lower than that of classical layout at low incoming Mach number,which is 1.7%lower when angle of attack is 4°.While at high incoming Mach number,the total drag force of inverted layout is higher than that of classical layout,which is 2.0% higher when angle of attack is 4°.

关 键 词：超声速进气道 “X”型布局 倒置进气道 正置进气道 气动性能比较 阻力特性 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]