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Experimental and Theoretical Investigations of Normal Shock Wave/Turbulent Boundary- Layer Interactions at Low Mach Numbers in a Square Straight Duct

机译：方直管中低马赫数下正常冲击波/湍流边界层相互作用的实验和理论研究

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《AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition》|2009年|P.1-11|共11页
会议地点 Orlando FL(US)
作者
Y. Miyazato; K. Matsuo; R. Kasada;
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作者单位

The University of Kitakyushu Kitakyushu Japan;

IDEC Corporation Osaka Japan;

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1. Numerical and Experimental Investigations on Mach 2 and 4 Pseudo-Shock Waves in a Square Duct [J] . Liqun SUN, Hiromu SUGIYAMA, Kazuhide MIZOBATA, Transactions of the Japan society for aeronautical and space sciences . 2004,第156期

机译：方管中2和4马赫伪冲击波的数值和实验研究
2. The influence of the laminar-turbulent transition on the interaction between the shock wave and boundary layer at a low supersonic Mach number [J] . Polivanov P. A., Sidorenko A. A., Maslov A. A. Technical physics letters: Letters to the Russian journal of applied physics . 2015,第10期

机译：低超声速马赫数下层流湍流对冲击波与边界层相互作用的影响
3. Experimental investigation of axisymmetric hypersonic shock-wave/turbulent- boundary-layer interactions [J] . Murray N., Hillier R., Williams S. Journal of Fluid Mechanics . 2013,第Null期

机译：轴对称高超声速激波/湍流边界层相互作用的实验研究
4. Experimental and Theoretical Investigations of Normal Shock Wave/Turbulent Boundary- Layer Interactions at Low Mach Numbers in a Square Straight Duct [C] . Y. Miyazato, K. Matsuo, R. Kasada American Institute of Aeronautics and Astronautics Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition . 2009

机译：方形直管中低马赫数正常冲击波/湍流边界层相互作用的实验与理论研究
5. AN EXPERIMENTAL INVESTIGATION OF SHOCK WAVES AND TURBULENT BOUNDARY LAYER INTERACTIONS IN A SUPERSONIC FLOWFIELD THROUGH AN ANNULAR DUCT (SCRAMJET). [D] . STOCKBRIDGE, RICHARD DREXEL. 1986

机译：通过环形管道（SCRAMJET）进行超音速流场中冲击波和湍流边界层相互作用的实验研究。
6. Experimental Control of Turbulent Boundary Layers with In-plane Travelling Waves [O] . James Bird, Matthew Santer, Jonathan F. Morrison -1

机译：面内行波湍流边界层的实验控制
7. Experimental Investigation on Flow Structure of Mach 4 Pseudo-Shock Wave in a Square Duct [O] . Koichi FUKUDA, Hiromu SUGIYAMA, Kazuhide MIZOBATA, 2003

机译：正方形管道马赫4伪冲击波流动结构的实验研究
8. TURBULENT BOUNDARY LAYERS IN COMPRESSIBLE FLOW ANDnTHEIR INTERACTIONS WITH NORMAL SHOCK WAVES A SURVEY AND PROPOSED INVESTIGATION [R] . W. H. SCHOFIELD 1970

机译：可压缩流动中的湍流边界层与正常冲击波的相互作用调查和建议的调查

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