超声速进气道起动性能影响因素研究  

Research on the Effects of Start Ability of Supersonic Inlet

作　　者：王利平[1] 孙振华[1] 贺永杰[1] 马高建[1] Wang Liping;Sun Zhenhua;He Yongjie;Ma Gaojian(China Airborne Missile Academy,Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2018年第4期39-45,共7页Aero Weaponry

摘　　要：从影响进气道起动性能的全因素出发,建立一体化模型,研究来流马赫数、攻角、侧滑角对进气道起动性能的影响,对进气道转级过程进行了动态过程仿真。结果表明,随着来流马赫数的增大,进气道流量系数与总压恢复系数变化趋势相反,应选择合适的设计马赫数,拓宽进气道的工作包线;随着侧滑角的增大,背风侧进气道起动性能及抗反压性能下降;转级过程中,背风侧超临界裕度明显小于迎风侧,研制过程中,应按照背风侧进气道进行超临界裕度设计。From the factors influence on starting ability of inlet , the integrative model is built, and the starting performance of inlet with dirt）rent Mach number, attack angle, side slip angle are investigated, the dynamic process of transition is simulated. The results show that, with the increase of the Mach number, flow coefficient and total pressure recovery coefficient had opposite tendency, it is important to choose appropriate design Mach number, and wide the operating envelope. With the increase of side slip angle, the start ability and resisting back pressure ability of leeward side inlet are decreased. During the transition process, the leeward side supercritical margin is significantly smaller than the windward side, so the supercritical margin should be designed according to the leeward side inlet.

关 键 词：进气道 起动性能 马赫数 攻角 侧滑角 动态过程 冲压发动机 

分 类 号：TJ763[兵器科学与技术—武器系统与运用工程] V43[航空宇航科学与技术—航空宇航推进理论与工程]