一种平面埋入式进气道的地面工作特性及流态特征

孙姝; 郭荣伟; 伍贻兆

一种平面埋入式进气道的地面工作特性及流态特征

南京航空航天大学航空宇航学院, 南京 210016

计量
- 文章访问数: 1689
- HTML浏览量: 151
- PDF量: 454
- 被引次数: 0
出版历程
- 收稿日期: 2006-06-28
- 修回日期: 2006-11-15
- 刊出日期: 2007-03-28

Experimental and computational study of a submermerged inlet on the plane surface under ground running

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 对一种平面埋入式进气道的地面工作特性进行了实验研究, 结合数值仿真技术, 分析了地面工作状态下该类进气道的流态特征, 并探讨了其出口总压图谱的形成成因.结果表明:(1)虽然进气道出口截面的二次流较弱, 但通道内却存在强的以对涡为特征的旋流, 该对涡因埋入式进气道进口侧棱的存在而产生, 与后唇口前缘的气流分离共同导致了进气道出口截面的大面积低总压区;(2)地面工作状态下, 埋入式进气道的总压恢复系数随出口马赫数的上升而下降, 周向畸变指数、紊流度和综合畸变指数则随着出口马赫数的增加而增加.在相同的出口马赫数下, 地面工作状态的总压恢复系数高于飞行状态, 各种畸变指数也明显偏高.但当发动机的进口工作马赫数为0.35左右时, 进气道出口截面的综合畸变指数W小于10.0%, 满足常规发动机的稳定工作要求;(3)计算和实验结果对比表明, 所得到的进气道出口总压恢复系数相对误差在1.2%以内, 但畸变指数整体偏大.
- 航空、航天推进系统 /
- 平面埋入式进气道 /
- 地面工作状态 /
- 对涡 /
- 总压恢复系数
Abstract: Utilizing the combined experimental and computational method,the aerodynamic performance and internal flow pattern of a submerged inlet on the plane surface under ground running are obtained in this paper.Results indicate that:(1) The secondary flow at the cross sections behaves as two counter-rotating vortices which are originated by the side edge of the entrance.The ongoing vortex pair interacts with the separated flow near the aft lip of the inlet and results in the low total pressure region at the bottom surface of the exit.(2)With the ascent of Mach number at the exit,both the total pressure loss and distortion index increases.In spite of a remarkable shift of the distortion index under ground running,compared with high speed wind tunnel tests,the synthesis distortion index is kept below 10.0% at the maximum RPM which does not threaten the stable operation of the engine.(3) The CFD results agree well with the experiment and the relative errors of the total pressure coefficient is less than 1.2% though the distortion index by CFD is a bit higher.
- aerospace propulsion system /
- submerged inlet on the plane /
- ground running /
- vortex pair /
- the synthesis distortion

HTML

参考文献(18)

[1]	Seddon J,Goldsmith E L.Intake aerodynamics[M].1st ed.,AIAA Education Series,Collins Professional and Technical Books,New York:1985.
[2]	Randall L M,Mossman E A.An experimental investigation of the design variables for NACA[R].NACA RM-A7130,Jan.,1948.
[3]	Frick C W,Davis W F.An experimental investigation of NACA submerged-duct entrances[R].NACA ACR-5120,Nov.,1945.
[4]	郭荣伟,刘少永.埋入式进气道设计[J].南京航空航天大学学报,2002,33(1):8-12.GUO Rongwei,LIU Shaoyong.Design of submerged inlet[J].Journal of Nanjing University of Aeronautics and Astronautics,2002,33(1):8-12.
[5]	余安远,郭荣伟.一种隐身外形弹体下埋入式进气道的进气机理与低速实验研究[J].空气动力学报,2003,21(2):182-188.YU Anyuan,GUO Rongwei.Air-admission mechanism and low speed tunnel test of a submerged inlet with low RCS missile body[J].Acta Aerodynamic Snica,2003,21(2):182-188.
[6]	Jovanovic V J,Taskinoglu E S,Knight D,et al.Experimental investigation of a submerged subsonic inlet[R].AIAA-2004-2649,2004.
[7]	杨爱玲,郭荣伟.埋入式进气道设计及气动性能研究[J].空气动力学报,1998,16(2):154-161.YANG Ailing,GUO Rongwei.An investigation on design and performance for a submerged air inlet[J].Acta Aerodynamic Snica,1998,16(2):154-161.
[8]	余安远,郭荣伟.隐身外形飞行器用埋入式进气道设计及起动性能研究[D].南京:南京航空航天大学,南京,2003.YU Anyuan,GUO Rongwei.A study of the design and flow characteristics for a submerged inlet under a stealthy shaped fuselage[D].Nanjing University of Aeronautics and Astronautics,Nanjing:2003.
[9]	孙姝,郭荣伟.平面埋入式进气道口面参数选择与试验验证[J].航空学报,2005,26(3):268-275.SUN Shu,GUO Rongwei.Experimental research of effects of entrance parameters on performance of submerged Inlet[J].Acta Aeronautica et Astronautica Snica,2005,26(3):268-275.
[10]	杨爱玲,郭荣伟.二维埋入式进气道的数值分析[J].航空学报,1998,16(2):154-161.YANG Ailing,GUO Rongwei.Numerical simulation of the flow of two dimensional submerged air inlet[J].Acta Aeronautica et Astronautica Snica,1999,20(5):450-454.
[11]	Taskinoglu E S,Knight D.Numerical analysis of submerged inlets[R].AIAA 2002-3147,2002.
[12]	Taskinoglu E S,Knight D.Design optimization for submerged inlets-part Ⅰ[R].AIAA 2003-1247,2003.
[13]	Taskinoglu E S,Knight D.Design optimization for submerged inlets-part Ⅱ[R].AIAA 2003-3926,2003.
[14]	Taskinoglu E S,Knight D.Multi-objective shape optimization study for a subsonic submerged inlet[J].Journal of Propulsion and Power,2004,20(4):448-456.
[15]	SUN Shu,GUO Rongwei.Numerical analysis and experimental validation of a submerged inlet on the plane surface[J].Chinese Journal of Aeronautics,2005,18(3):199-205.
[16]	谭慧俊,郭荣伟.一种双斜切双压缩面进气道地面流态的数值模拟研究[J].航空学报,2002,23(3):197-205.TAN Huijun,GUO Rongwei.Numerical simulation of a dual-swept/D ual-ramp inlet under ground running[J].Acta Aeronautica et Astronautica Snica,2002,23(3):197-205.
[17]	谭慧俊,郭荣伟.一种背负式无附面层隔道进气道的数值模拟与试验验证[J].航空学报,2004,25(6):540-545.TAN Huijun,GUO Rongwei.Numerical investigation of a Top-Mounted Diverterless Inlet and its Validation[J].Acta Aeronautica et Astronautica Snica,2004,25(6):540-545.
[18]	TAN Huijun,GUO Rongwei.Design and wind tunnel study of a top-mounted diverterless inlet[J].Chinese Journal of Aeronautics,2004,17(2):72-78.