Volume 27 Issue 6
Jun.  2012
Turn off MathJax
Article Contents
LI Yong-zhou, Zhang Kun-yuan, NAN Xiang-jun, ZHANG Lin. Design and numerical investigation of hypersonic inward turning inlet with water-drop like shape intake[J]. Journal of Aerospace Power, 2012, 27(6): 1355-1361.
Citation: LI Yong-zhou, Zhang Kun-yuan, NAN Xiang-jun, ZHANG Lin. Design and numerical investigation of hypersonic inward turning inlet with water-drop like shape intake[J]. Journal of Aerospace Power, 2012, 27(6): 1355-1361.

Design and numerical investigation of hypersonic inward turning inlet with water-drop like shape intake

  • Received Date: 2011-06-25
  • Publish Date: 2012-06-28
  • The water-drop like shape to circular shape transition hypersonic inward turning inlet has been designed with the technology of streamline tracing and gradual change section,using an axisymmetric basic flowfield with controllable pressure rising distribution.Numerical simulations were conducted on both design point and translation point,and the comparison of performance was performed with the rectangular to circular shape transition inward turning inlet with the same design parameters.The results indicate that two types of inward turning inlet have the roughly equivalent general performance,while the water-drop like shape intake has a more uniform exit flowfield and a better starting characteristic.Furthermore,the flowfiled structure of water-drop like shape intake is asymmetric due to the asymmetric geometry shapes.

     

  • loading
  • [1]
    Voland R T,Auslende A H,Smart M K.CIAM/NASA Mach 6.5 scramjet flight and ground test .AIAA 1999-4848,1999.
    [2]
    Trexler C A.Performance of an inlet for an integrated scramjet concept[J].Aircraft,1974,11(9):589-591.
    [3]
    Molder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
    [4]
    Van Wie D M,Molder S.Applications of Busemann inlet designs for flight at hypersonic speeds .AIAA 1992-1210,1992.
    [5]
    Billig F S.SCRAM-A supersonic combustion ramjet missile .AIAA 1993-2329,1993.
    [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):396-399. 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,2007,22(3):396-399.(in Chinese)
    [7]
    Bulman M J,Siebenhaar A.The rebirth of round hypersonic propulsion .AIAA 2006-5035,2006.
    [8]
    Walker S H,Rodgers F C,Esposita A L.Hypersonic collaborative Australia/United States experiment (HYCAUSE) .AIAA 2005-3254,2005.
    [9]
    Elvin J D.Integrated inward turning inlets and nozzles for hypersonic air vehicles:US,20070187550A1.3 .2007-08-16.
    [10]
    Walker S H,Rodgers F.Falcon hypersonic technology overview .AIAA 2005-3253,2005.
    [11]
    Billig F S,Jacobsen L S.Comparison of planar and axisymmetric flowpaths for hydrogen fueled space access vehicle .AIAA 2003-4407,2003.
    [12]
    Smart M K.Design of three-dimensional hypersonic inlets with rectangular-to-elliptical shape transition[J].Journal of Propulsion and Power,1999,15(3):408-416.
    [13]
    Sabean J,Lewis M J.Optimization of a hypersonic inlet with a rectangular to circular transition .AIAA 1999-0612,1996.
    [14]
    Dissel A F,Kothari A P.Investigation of two-stage-to-orbit air breathing launch-vehicle configurtions[J].Spacecraft Rockets,2006,43(3):568-574.
    [15]
    NAN Xiangjun,ZHANG Kunyuan.Numerical and experimental investigation on hypersonic inward turning inlets with basic flow field using arc tangent curve law of pressure rise .AIAA 2011-2270,2011.
    [16]
    南向军,张堃元,金志光,等.压升规律可控的高超声速内收缩进气道设计[J].航空动力学报,2011,26(3):518-523. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,2011,26(3):518-523.(in Chinese)
    [17]
    南向军,张堃元,金志光,等.矩形转圆形高超声速内收缩进气道数值及实验研究[J].航空学报,2011,32(6):988-996. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Numerical and experimental investigation of hypersonic inward turning inlets with rectangular to circular shape transition[J].Acta Aeronautica et Astronautica Sinica,2011,32(6):988-996.(in Chinese)
    [18]
    Bagaveyev N T,Engbom W A,Bhagwandin V A.Parametric investigation of racetrack-to-circular cross section transition of a dual-mode ramjet isolator .AIAA 2010-0942,2010.
  • 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

    Article Metrics

    Article views (1846) PDF downloads(493) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return