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Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer II : effect of an oblique shock wave immediately ahead of the inlet

机译：通过位于明显边界层II区域的环形管道入口以超音速恢复压力：在入口前方的倾斜冲击波的影响

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Brajnikoff, George B;
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年度 1948
页码 1-16
总页数 16
原文格式 PDF
正文语种 eng
中图分类工业技术;
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1. Flow Simulation of Supersonic Inlet with Bypass Annular Duct [J] . HyoungJin Kim, Takayasu Kumano, Meng-Sing Liou, Journal of propulsion and power . 2011,第1期

机译：超音速进气道绕过环形通道的流动模拟
2. Flow Simulation of Supersonic Inlet with Bypass Annular Duct [J] . Hyoungjin Kim, Takayasu Kumano, Meng-Sing Liou, Journal of Propulsion and Power . 2011,第1期

机译：超音速进气道绕过环形通道的流动模拟
3. Influence of Expansion Waves on Cowl Shock/Boundary Layer Interaction in Hypersonic Inlets [J] . Yue Zhang, Hui-jun Tan, Yi Zhuang, Journal of propulsion and power . 2014,第5期

机译：膨胀波对高超声速进气道面罩冲击/边界层相互作用的影响
4. Control Volume Analysis of Boundary Layer Ingesting Propulsion Systems With or Without Shock Wave Ahead of the Inlet [C] . Hyun Dae Kim, James L. Felder AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition . 2011

机译：入口处有或没有冲击波的边界层进水推进系统的控制体积分析
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. Control of shock wave-boundary layer interactions by bleed in supersonic mixed compression inlets [O] . Fukuda, M. K., Hingst, W. G., Reshotko, E. 1975

机译：通过超声速混合压缩入口中的排气控制冲击波边界层相互作用

Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer II : effect of an oblique shock wave immediately ahead of the inlet

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