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矩形截面高超声速进气道气动设计及实验验证 被引量:13

Design and Experimental Verification of Hypersonic Inlet with Rectangular Section
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摘要 首先对矩形截面高超声速进气道设计方法进行了研究,给出了设计流程,并据此设计了矩形截面高超声速进气道。接着对其进行了三维数值仿真研究,给出了进气道性能参数随来流马赫数、飞行迎角及飞行高度的变化规律。最后设计了实验模型,并进行了高焓风洞实验验证。数值模拟及高焓风洞实验验证均表明:本文采用的设计方法可达到预期的设计效果,设计的进气道达到了相应的设计要求;本文采用的数值仿真方法可以较为准确地模拟高超声速进气道内的流动,数值模拟结果可信。 The design method for a hypersonic inlet with a rectangular section is presented and the inlet is designed at the point of Ma = 6.0. The flow in the hypersonic inlet is analyzed with a three-dimensional numerical analyzer. The flow characteristics at different Mach numbers, attack angles and flying attitudes are also discussed. The preliminary test verification is conducted in the hypersonic inlet at Ma = 6 in a high enthalpy tunnel. The total pressure and static pressure distributions in flow of the inlet are obtained and compared with the calculation data. The result shows that the numerical results have basic flow characteristics. Both the numerical simulation and the experimental result show that the design method is feasible for the hypersonic inlet with the rectangular section.
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2009年第4期423-428,共6页 Journal of Nanjing University of Aeronautics & Astronautics
基金 国家高技术发展研究计划("八六三计划")资助项目
关键词 高超声速进气道 设计方法 矩形截面 实验验证 hypersonic inlet design method rectangular section experimental verification
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  • 1梁德旺,王可.AUSM+格式的改进[J].空气动力学学报,2004,22(4):404-409. 被引量:26
  • 2[1]Wahrup P J,Biliig F S.Structure of shock waves in cylindrical ducts[J].AIAA Journal,1973,11(10):1404-1408.
  • 3[2]Bement D A,Stevens J R,Thompson M W.Measured Operating Characteristics of a Roctangular Combustor/Inlet Isolator[R].MAA 90-2221,1990.
  • 4[3]Lin P,Rao G V R,O'Connor G M.Numerical Analysis of Normal Shock Train in a Constant Area Isolator[R].AIAA 91-2162,1991.
  • 5[5]Carroll B F,Dutton J C.Characteristics of multiple shock wave/tur-bulent boundary-layer interactions[J].Journal of Propulsion and Power,1992,8(2):441-448.
  • 6[6]Carroll B F,Dutton J C.Characteristics of multiple shock wave/tur-bulent boundary-layer interactions in rectangular ducts[J].Journal of Propulsion and Power,1990,6(2):186-193.
  • 7[9]Kazuyasu Matsuo.Yoshiaki miyazato and heuy-dong kim,Shock train and pseudo-shock phenomena in internal gas flows[J],Progress in Aerospace Sciences,1999,35:33-100.
  • 8Emami S, Trexler A, Auslender H, et al. Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4[R].NASA-TP-3502.
  • 9Holland D. Wind-tunnel blockage and actuation systems test of a two-dimensional scram jet inlet unstart model at mach 6[R]. NASA-TM-109152.
  • 10Van Wie D M, Kwok F T, Walsh R F. Starting charateristics of supersonic inlets [R]. AIAA-96-2914, 1996.

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