Volume 26 Issue 3
Mar.  2011
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2011  >  26(3): 518-523
NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang, SUN Bo. Investigation on hypersonic inward turning inlets with controlled pressure gradient[J]. Journal of Aerospace Power, 2011, 26(3): 518-523.
Citation: NAN Xiang-jun, ZHANG Kun-yuan, JIN Zhi-guang, SUN Bo. Investigation on hypersonic inward turning inlets with controlled pressure gradient[J]. Journal of Aerospace Power, 2011, 26(3): 518-523.
shu

Investigation on hypersonic inward turning inlets with controlled pressure gradient

  • 1.

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

  • 2.

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

  • 3.

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

  • 4.

    Department of Aerospace Engineering,School of Mechanical Engineering, Nanjing University of Science and Technology,Nanjing 210094,China

  • Received Date: 2010-03-22
  • Rev Recd Date: 2010-05-28
  • Publish Date: 2011-03-28
    Abstract
  • Axisymmetric basic flowfields with controlled pressure gradient used for hypersonic inward turning inlets were investigated using the rotational method of characteristics.In combination with streamline tracing technique,a circular inward turning inlet with the law of constant pressure gradient was designed and numerically simulated.Results show that the inward turning inlet could maintain the same law of pressure rise as its basic flowfield.Through study of the three laws of wall pressure rise,pressure gradient increase,steadiness and decrease,it's found the inlet with the first law of pressure rise has the maximum compression efficiency,and the inlet with the third law of pressure rise has the lowest compression efficiency.In addition,we can get good internal and external compression assignment by adjusting the law of pressure rise,contributing to make this type of inlet operate well over a large wide range of Mach number.

     

    • FullText(HTML)
  • loading
    • References(13)
  • [1]
    Mlder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
    [2]
    Mlder S.Internal,axisymmetric,conical flow[J].AIAA Journal,1967,5(7):1252-1255.
    [3]
    Billig F S.SCRAM—A supersonic combustion ramjet missile .AIAA Paper 93-2329,1993.
    [4]
    Sun B,Zhang K Y,Wang C P,et al.Investigation on a streamtraced hypersonic busemann inlet[J].Aerospace Engineering,2009,224(1):57-63.
    [5]
    Jacobsen L S,Tam C J,Behadnia R,et al.Starting and operation of a streamline-traced busemann inlet at Mach 4 .AIAA 2006-4508,2006.
    [6]
    孙波,张堃元,金志光.流线追踪Busemann 进气道马赫数3.85 实验研究[J].航空动力学报,2007,22(3):128-131. SUN Bo,ZHANG Kunyuan,JIN Zhiguang.Experimental research of Mach 3.85 performance of a streamline traced hypersonic Busemann inlet[J].Journal of Aerospace Power,2006,22(3):128-131.(in Chinese)
    [7]
    Molder S,Timofeev E V,Tahir R B.Flow starting in high compression hypersonic air inlets by mass spillage .AIAA 2004-4130,2004.
    [8]
    Smart M K.Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition .AIAA 98-0960,1998.
    [9]
    Smart M K.Experimental testing of a hypersonic inlet with rectangular-to-elliptical shape transition .AIAA 99-0085,1999.
    [10]
    Matthews A J,Jones T V.Design and test of a modular waverider hypersonic intake .AIAA 2005-3379,2005.
    [11]
    You Y C,Liang D W,Guo R W.High enthalpy wind tunnel tests of three-dimensional section controllable internal waverider hypersonic inlet .AIAA Paper 2009-31,2009.
    [12]
    Hornung H G.Oblique shock reflection from an axis of symmetry[J].Fluid Mech.,2001,409(1):1-12.
    [13]
    Travis W D,Ioannis N,Graham V C.Hypersonic inward turning inlets:design and optimization .AIAA 2006-297,2006.
    • 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(1067.0KB)
    XML

    Article Metrics

    Article views (2423) PDF downloads(52) 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