Volume 27 Issue 5
May  2012
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2012  >  27(5): 1131-1138
CHENG Dai-shu, SUN Shu, WEN Yu-fen, TAN Hui-jun. Submerged inlet performance improvement with blowing on fuselage[J]. Journal of Aerospace Power, 2012, 27(5): 1131-1138.
Citation: CHENG Dai-shu, SUN Shu, WEN Yu-fen, TAN Hui-jun. Submerged inlet performance improvement with blowing on fuselage[J]. Journal of Aerospace Power, 2012, 27(5): 1131-1138.
shu

Submerged inlet performance improvement with blowing on fuselage

  • 1.

    College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • 2.

    College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

  • Received Date: 2011-06-08
  • Publish Date: 2012-05-28
    Abstract
  • Due to the large amount of boundary layer ingested into the submerged inlet which results in low total pressure recovery and high flow distortion,a flow control method based on blowing on the fuselage was introduced.By computational method,the models without and with inlet were both studied to obtain the effects of blow technique on the performance and flow structure of submerged inlet.Results indicate that the control method is effective to blow fuselage boundary layer,and improve the boundary layer condition before entrance and the flow in the duct.At the design condition,the total pressure recovery coefficient increased by 1.5% and the distortion index decreased by 6.6% as compared with the baseline case.

     

    • FullText(HTML)
  • loading
    • References(14)
  • [1]
    李学来.埋入式进气道的技术现状[J].福州大学学报:自然科学版,2001,29(6):61-66. LI Xuelai.Development of submerged intake[J].Journal of Fuzhou University (Natual Science Edition),2001,29(6):61-66.(in Chinese)
    [2]
    Mossman E A,Randall L M.An experimental investigation of the design variables for NACA.NACA RM-A7I30,1948.
    [3]
    Hall C F,Frank J L.Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds.NACA RM-A8I29,1948.
    [4]
    Axelson J A,Taylor R A.Preliminary investigation of the transonic characteristics of an NACA submerged inlet.NACA RM-A50C13,1950.
    [5]
    Frank J L.Pressure-distribution and Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds.NACA RM-A50E02,1950.
    [6]
    Anderson W E,Frazer A C.Investigation of an NACA submerged inlet at Mach numbers from 1.17 to 1.99.NACA RM-A52F17,1952.
    [7]
    任三星.埋入式进气道设计与流场控制研究.南京:南京航空航天大学,1993 REN Sanxing.Design and flow control investigation of a submerged air intake.Nanjing:Nanjing University of Aeronautics and Astronautics,1993.(in Chinese)
    [8]
    Taskinoglu E S,Knight D.Design optimization for submerged inlets PartⅠ.AIAA 2003-1247,2003.
    [9]
    Taskinoglu E S,Knight D.Design optimization for submerged inlets Part Ⅱ.AIAA 2003-3926,2003.
    [10]
    Taskinoglu E S,Jovanovic V,Knight D.Multi-objective design optimization and experimental measurement for a submerged inlet.AIAA 2004-0025,2004.
    [11]
    Jovanovic V,Taskinoglu E S,Knight D.Experimental investigation of a submerged subsonic innlet.AIAA 2004-2649,2004.
    [12]
    Taskinoglu E S,Knight D.Multi-objective shape optimization study for a subsonic submerged inlet[J].Journal of Propulsion and Power,2004,20(4):620-633.
    [13]
    余安远,郭荣伟,孙姝,等.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, SUN Shu, et al. Air- admission mechanism and low speed tunnel test fo a submerged inlet with low RCS missile body[J].Acta Aerodynamic Snica,2003,21(2):182-188.(in Chinese)
    [14]
    Sun S,Guo R W.Numerical analysis and experimental validation of a submerged inlet on the plane surface [J].Chinese Journal of Aeronautics,2005,18(3):199-205.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(1046.0KB)
    XML

    Article Metrics

    Article views (1908) PDF downloads(654) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return