Volume 29 Issue 9
Sep.  2014
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ZHANG Lin, ZHANG Kun-yuan, WANG Lei, LI Yong-zhou. Numerical simulation of two-dimensional curved compression surface with isentropic surface coordinate transformation[J]. Journal of Aerospace Power, 2014, 29(9): 2031-2039. doi: 10.13224/j.cnki.jasp.2014.09.003
Citation: ZHANG Lin, ZHANG Kun-yuan, WANG Lei, LI Yong-zhou. Numerical simulation of two-dimensional curved compression surface with isentropic surface coordinate transformation[J]. Journal of Aerospace Power, 2014, 29(9): 2031-2039. doi: 10.13224/j.cnki.jasp.2014.09.003

Numerical simulation of two-dimensional curved compression surface with isentropic surface coordinate transformation

doi: 10.13224/j.cnki.jasp.2014.09.003
  • Received Date: 2013-05-26
  • Publish Date: 2014-09-28
  • Different coordinate transformation matrixes were used to scale the coordinate of isentropic surface, and a series of two-dimensional curved compression surfaces with different curvature were obtained. The curved compression surfaces were studied using numerical simulation, and then compared with the curved compression surfaces with wall Mach number linear distribution and controllable law of pressure rise. The result shows that: the surface length can be shortened obviously due to coordinate transformation of isentropic surface, and the curved compression surface length scaled using x axis scaling factor of 0.7 can be reduced by 30% at the same total turning angle. The curved compression surfaces with different x axis scaling factors produce dispersed compression waves that will not be converged to one point, and the isentropic compression flow characteristics can be kept. Wall pressure distribution is improved to a certain extent and wall Mach number distribution tends to be linear with decreasing x axis scaling factor. The curved compression surfaces with x axis scaling factor of 0.5 and wall Mach number linear distribution have similarity in the flowfield structure, wall pressure, wall Mach number distribution, exit total pressure recovery coefficient and exit Mach number distribution.

     

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  • [1]
    Curran E T.Scramjet engines:the first forty years[J].Journal of Propulsion and Power,2001,17(6):1138-1148.
    [2]
    Oswatitsch K.Pressure recovery in missiles with reaction propulsion at high supersonic speeds[R].NACA TM1140,1947.
    [3]
    Henderson L F.Maximum total pressure recovery across a system of n shock waves[J].AIAA Journal,1964,2(6):1138-1140.
    [4]
    Connors J F,Meyer R C.Design criteria for axisymmetric and two-dimensional supersonic inlets and exits[R].NACA TN 3589,1956.
    [5]
    Heiser W H,Pratt D T,Daley D H,et al.Hypersonic air-breathing propulsion[M].Washington:American Institute of Aeronautics and Astronautics Inc,1994.
    [6]
    Mölder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
    [7]
    Mölder S.Internal axisymmetric conical flow[J].AIAA Journal,1967,5(7):1252-1255.
    [8]
    Vijay R,Lewis M,Starkey R.Performance of various truncation strategies employed on hypersonic Busemann inlets[R].AIAA-2009-7249,2009.
    [9]
    Drayna T W,Nompelis I,Candler G V.Hypersonic inward turning inlets:design and optimization[R].AIAA-2006-297,2006.
    [10]
    Colville J R,Lewis M J.An aerodynamic redesign of the SR-71 inlet with applications to turbine based combined cycle engines[R].AIAA-2004-3481,2004.
    [11]
    张林,张堃元,王磊,等.基于壁面马赫数梯度的高超声速弯曲激波二维进气道数值研究[J].航空动力学报,2013,28(4):752-758. ZHANG Lin,ZHANG Kunyuan,WANG Lei,et al.Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient[J].Journal of Aerospace Power,2013,28(4):752-758.(in Chinese)
    [12]
    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)
    [13]
    向有志,张堃元,王磊,等.壁面压升可控的高超轴对称进气道优化设计[J].航空动力学报,2011,26(10):2193-2199. XIANG Youzhi,ZHANG Kunyuan,WANG Lei,et al.Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise[J].Journal of Aerospace Power,2011,26(10):2193-2199.(in Chinese)
    [14]
    张林,张堃元,王磊,等.新型高超弯曲激波二维进气道初步研究[J].航空动力学报,2011,26(11):2556-2562. ZHANG Lin,ZHANG Kunyuan,WANG Lei,et al.Preliminary study on hypersonic curved shock two-dimensional inlet[J].Journal of Aerospace Power,2011,26(11):2556-2562.(in Chinese)
    [15]
    金志光,张堃元.带前体压缩的前掠侧压式进气道实验及数值研究[J].推进技术,2005,26(6):508-512. JIN Zhiguang,ZHANG Kunyuan.Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression[J].Journal of Propulsion Technolgy,2005,26(6):508-512.(in Chinese)
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