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AN EXPERIMENTAL INVESTIGATION AT MACH NUMBERS FROM 2.1 TO 3.0 OF CIRCULAR INTERNAL-COMPRESSION INLETS HAVING TRANSLATABLE CENTERBODIES AND PROVISIONS FOR BOUNDARY-LAYER REMOVAL

机译：具有可转换中心体的圆形内压缩进口2.1至3.0的机械编号的实验研究和边界层去除的规定

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Inlets having translatable centerbodies and provision for boundary layer removal

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作者
Watson, E. C.;
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年度 1960
页码 1-27
总页数 27
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AIR INTAKES; ANNULI; BOUNDARY LAYER CONTROL; BOUNDARY LAYERS; CENTERBODIES; INTERNAL COMPRESSION INLETS; PERFORATION; SUPERSONIC SPEED; AIR INLET; BOUNDARY LAYER CONTROL;

机译：空气进入;环带;边界层控制;边界层; CENTERBODIEs;内部压缩入口;穿孔;超音速;空气入口;边界层控制;

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1. Experimental Investigation on Forced Boundary-Layer Transition of Axisymmetric Inlet and Numerical Verification [J] . Fan Xiao-qiang, Li Hua, Jia Di, Journal of Aircraft . 2006,第5期

机译：轴对称入口强迫边界层过渡的实验研究及数值验证
2. Time-Accurate Experimental Investigation of Hypersonic Inlet Buzz at Mach 5 [J] . Berto Federico, Benini Ernesto, Wyatt Ciaras, AIAA Journal . 2020,第5期

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3. Experimental investigation of effects of mach number on the flow instability in a supersonic inlet [J] . Soltani M.R., Farahani M. Experimental Techniques . 2013,第3期

机译：马赫数对超音速进气道流动不稳定性影响的实验研究
4. Experimental Investigation of Starting Process for a Variable Geometry Air Inlet operating from Mach 2 to Mach 8 [C] . F. Falempin, E. Wendling, M. Goldfeld, AIAA/ASME/SAE/ASEE Joint Propulsion Conference Exhibit . 2006

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5. Experimental pressure and heat transfer investigation over a "directed-energy air spike" inlet at flow mach numbers of 10 to 20, stagnation temperature of 1000 K, and arc powers up to 127 KW. [D] . Toro, Paulo Gilberto de Paula. 1998

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6. CFD Analysis to Study Effect of Circular Vortex Generator Placed in Inlet Section to Investigate Heat Transfer Aspects of Solar Air Heater [O] . Vipin B. Gawande, A. S. Dhoble, D. B. Zodpe -1

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7. Reynolds Number and Cowl Position Effects for a Generic Sidewall Compression Scramjet Inlet at Mach 10: A Computational and Experimental Investigation [O] . Holland Scott D. 1992

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AN EXPERIMENTAL INVESTIGATION AT MACH NUMBERS FROM 2.1 TO 3.0 OF CIRCULAR INTERNAL-COMPRESSION INLETS HAVING TRANSLATABLE CENTERBODIES AND PROVISIONS FOR BOUNDARY-LAYER REMOVAL

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