Volume 23 Issue 4
Apr.  2008
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CAI Qiao-yan, TAN Hui-jun. Effects of the forebody boundary layer state on flow structure and performance of hypersonic inlets[J]. Journal of Aerospace Power, 2008, 23(4): 699-705.
Citation: CAI Qiao-yan, TAN Hui-jun. Effects of the forebody boundary layer state on flow structure and performance of hypersonic inlets[J]. Journal of Aerospace Power, 2008, 23(4): 699-705.

Effects of the forebody boundary layer state on flow structure and performance of hypersonic inlets

  • Received Date: 2007-04-04
  • Rev Recd Date: 2007-07-23
  • Publish Date: 2008-04-28
  • Influences of the forebody boundary layer state on shock pattern,characteristics of shock/boundary-layer interaction,mass capture capability and total pressure recovery of axisymmetric hypersonic inlet were studied with the aids of CFD.The performance trend in accordance with the forced transition position was obtained at different Mach numbers.As a forced transition device,two-dimensional roughness was introduced to examine the disturbance it made to the flow field.Differences between specific inlet design schemes were also compared in the study.

     

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  • [1]
    Scott A B,Michael D F,Matthew K K.Forced boundary-Layer transition on X-43 (Hyper-X) in NASA LaRC 31-Inch Mach 10 air tunnel[R].NASA/TM-2000-210315,2000.
    [2]
    McClinton C R,Rausch V L,Nguyen L T,et al.Preliminary X-43 fight test results[J].Acts Astronautics 2006,57:266-276.
    [3]
    Steven P S.Hypersonic laminar-turbulent transition on circular cones and scramjet forebodies[J].Progress in Aerospace Sciences 2004,40:1-50.
    [4]
    Steven P S.Effects of high-speed tunnel noise on laminarturbulent Transition[J].J.Spacecraft and Rockets,2001,38(3):323-333.
    [5]
    Takeshi I,Laura A R,Steven P S.Effect of freestream noise on roughness-induced boundary-layer transition for a scramjet inlet[R].AIAA Paper 2000-0284,2000.
    [6]
    Steven P S.Flight data for boundary-layer transition at hypersonic and supersonic speeds[J].J.Spacecraft and Rockets,1999,36(1):8-20.
    [7]
    Scott A B,Michael D F,Matthew K K.Forced boundarylayer transition on X-43 (Hyper-X) in NASA LaRC 20-Inch Mach 6 air tunnel[R].NASA/TM-2000-210316,2000.
    [8]
    Voland R T,Auslender A H,Smart M K.CIAM/NASA Mach 6.5 scramjet flight and ground test[R].AIAA Paper 1999-4848,1999.
    [9]
    Rodriguez C G.CFD analysis of the ciam/nasa scramjet[R].AIAA Paper 2002-4128,2002.
    [10]
    谭慧俊,郭荣伟.高超声速混合模块冲压发动机亚燃模块进气道的高焓风洞实验研究[J].航空学报,2007,28(4):783-790.TAN Huiun,GUO Rongwei.Wind tunnel tests of hypersonic inlets for ramjet modules of ramjet scramjet combined engine[J].Acta Aeronautica et Astronautica Sinica,2007,28(4):783-790.
    [11]
    Paciorri R,Dieudonné W,Degrez G.Validation of the Spalart-Allmaras turbulence model for application in hypersonic flows[R].AIAA Paper 1997-2023,1997.
    [12]
    Elias T I,Eisworth E A.Stability studies of planar transition in supersonic flows[R].AIAA Paper 1990-5233,1990.
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