Volume 22 Issue 8
Aug.  2007
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ZHANG Xiao-jia, LIANG De-wang, LI Bo, YUAN Hua-cheng. Study of design method of typical two-dimensional hypeisonic inlet[J]. Journal of Aerospace Power, 2007, 22(8): 1290-1296.
Citation: ZHANG Xiao-jia, LIANG De-wang, LI Bo, YUAN Hua-cheng. Study of design method of typical two-dimensional hypeisonic inlet[J]. Journal of Aerospace Power, 2007, 22(8): 1290-1296.

Study of design method of typical two-dimensional hypeisonic inlet

  • Received Date: 2006-08-08
  • Rev Recd Date: 2007-03-15
  • Publish Date: 2007-08-28
  • A feasible design principle was developed by combining a series of design and performance predicting methods of typical two-dimensional hypersonic inlets.The design methods of inlet entrance, external compression shocks, internal contraction tunnel, cowl and isolator were presented at the given flux, pressure rise ratio and working range(starting Mach number and capability of enduring back pressure).A preliminary design of hypersonic inlet at the design point of H=22 800 m, Ma0=6 was conducted, so the performance parameters(pressure rise ratio, Mach number, temperature rise ratio and total pressure recovery), starting Mach number and capability of enduring back pressure were predicted and calculated with small error.With this method, the inlet could present simple construction, high flow coefficient and low compression loss in developing a satisfactory model without optimization.

     

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  • [1]
    Heiser W H,Pratt D T,DELEY D H,et al.Hypersonic air-breathing propulsion[M].Washington,D.C:American Institute of Aeronautics and Astronautics Inc,1994.
    [2]
    Craddock C S.Computational optimization of scramjets and shock tunnel nozzles[D].Queensland:Univ.of Queensland,1999.
    [3]
    XU Xu,XU Dajun,CAI Guobiao.Optimization design for scramjet and analysis of its operation performance[J].Acta Astronautica,2005,57:390-403.
    [4]
    车竞,唐硕.高超声速飞行器机身/超燃冲压发动机设计方法研究[J].试验流体力学,2006,20(2):41-49.CHE Jing,TANG Shuo.Research of airframe/scramjet integrated design of hypersonic vehicle[J].Journal of Experiments in Fluid Mechanics,2006,20(2):41-49.
    [5]
    黎明,宋文艳,贺伟.高超声速二维混压式前体/进气道设计方法研究[J],航空动力学报,2004,19(4):459-465.LI Ming,SONG Wenyan,HE Wei.Design method of two-dimensional hypersonic forebody/inlet of mixed Compression[J].Journal of Aerospace Power,2004,19(4):459-465.
    [6]
    梁德旺,李博.高超声速进气道隔离段反压的前传模式及最大工作反压[J].空气动力学学报,2006,24(4):454-460.LIANG Dewang,LI Bo.Back pressure propagation mode and maximum working back pressure of hypersonic inlet isolator[J].Acta Aerodynamica Sinica,2006,24(4):454-460.
    [7]
    梁德旺,李博,袁化成.反压作用下等直隔离段性能估算方法研究[C]//中国第一届近代空气动力学与气动热力学会议论文集.北京:国防工业出版社,2006.LIANG Dewang,LI Bo,YUAN Hua-cheng.Predicting method of the performance for constant area isolator under back pressure[C]//Proceedings of china 1st modern aerodynamics & aerothermodynamics conference.Beijing:National Deferce Industry Press,2006.
    [8]
    张坤元,萧旭东,徐辉.高超侧压式进气道参数分析及实验研究[J].推进技术,1995(6):20-25.ZHANG Kunyuan,XIAO Xudong,XU Hui.Parametric analysis and experimental investigation on sidewall compression inlet[J].Journal of Propulsion Technology.1995,12(6):20-25.
    [9]
    Van Wie D M,Kwok F T,Walsh R F.Starting characteristics of supersonic inlets[R].32nd AIAA/ASME/SAE/ASEE,1996.
    [10]
    张晓嘉,梁德旺.内压缩通道几何参数对高超声速进气道性能的影响[J],南京航空航天大学学报,2005,37(6):685-689.ZHANG Xiaojia,LIANG Dewang.Performance effects of geometry parameters on hypersonic inlet[J].Journal of Nanjing University of Aeronautics and Astronautics,2005,37(6):685-689.
    [11]
    Kantrowitz A,Donaldson C.Preliminary investigation of supersonic differs[R].NACA WRL-713,1945.
    [12]
    Nestler D E,Daywitt J E.Boundary layer separation borrelations for hypersonic inlet analyses[R].GE Report AMJ-86-01,1986.
    [13]
    范晓樯,李桦,丁猛.三维超声速隔离段湍流内流场旋涡结构的数值模拟[J].国防科技大学学报.2001,23(6):5-8.FAN Xiaoqiang,LI Hua,DING Meng.Numerical simulation of 3D turbulent vortex structures in isolator[J].Journal of National University of Defense Technology,2001,23(6):5-8.
    [14]
    Oswatisch K.Pressure recovery in missiles with reaction propulsion at high supersonic speeds[R].NACA TM 1140,1947.
    [15]
    Berry S A,Auslender A H,Dilley A D,et al.Hypersonic boundary-layer trip development for hyper-X[R].AIAA-2000-4012.
    [16]
    梁德旺,李博.某典型二元高超声速进气道内二次流分析[J].推进技术,2005,27(4):714-719.LIANG Dewang,LI Bo.Analysis secondary vortex in a 2-D typical scramjet inlet[J].Journal of Propulsion Technology,2005,27(4):714-719.
    [17]
    Hass N E,Smart M K,Paul A.Flight data analysis of hy-Shot 2[R].AIAA 2005-3354,2005.
    [18]
    Emami S,Trexler C A,Auslender A H,et al,Experimental investigation of inlet-combustor isolators for a du-al-mode scramjet at a Mach number of 4[R].NASA TP 3502,1995.
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