基于边界层抽吸的埋入式进气道性能优化研究  

Research on Performance Optimization of Submerged Inlet Based on Boundary Layer Suction

作　　者：肖毅 沈亮 刘敏 杨昌发 Xiao Yi;Shen Liang;Liu Min;Yang Changfa(Jiangxi AviationResearchInstitute,Nanchang 330213,China)

机构地区：[1]江西航空研究院,江西南昌330213

出　　处：《航空科学技术》2022年第7期23-28,共6页Aeronautical Science & Technology

摘　　要：埋入式进气道具有隐身性能好、飞行阻力低等优点,此类进气道通常具有低速性能优良、高亚声速性能偏低的基本特征。为了提升飞机巡航状态下(H=11000m、Ma=0.6)的进气性能,在进气道前设计加装了边界层抽吸孔,重点分析了边界层抽吸位置及抽吸流量对进气道性能的影响规律。数值仿真结果表明,在进气道前适当位置进行边界层抽吸能够排出部分近壁面低能量气流,从而提高进气性能;随着边界层抽吸流量的增大,进气道性能逐渐增加;抽吸流量一定时,边界层抽吸位置对进气性能影响较小。因此,在进气道前设计边界层抽吸装置是提升埋入式进气道高速阶段进气性能的有效手段。Submerged inlet has the advantages of high stealth performance and low flight resistance,this kind of inlet usually has the basic characteristics of excellent low-speed performance and low high-speed performance.In order to improve the inlet performance of aircraft in cruise state(H=11000m,Ma=0.6),boundary layer suction holes are installed in front of the inlet,the effects of boundary layer suction position and suction flow rate on inlet performance are analyzed.The numerical simulation results show that the boundary layer suction in front of the inlet can discharge some low-energy airflow near the wall so as to improve the inlet performance.However,when the suction flow is constant,the suction position of the boundary layer has little effect on the inlet performance.Therefore,the design of boundary layer suction device in front of the inlet is an effective means to improve the inlet performance of the submerged inlet in the high-speed stage.

关 键 词：埋入式进气道 边界层抽吸 数值仿真 性能优化 总压恢复系数 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]