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首页> 美国政府科技报告 >Experimental Investigation of the Performance of a Mach-2.7 Two-DimensionalBifurcated Duct Inlet with 30 Percent Internal Contraction
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Experimental Investigation of the Performance of a Mach-2.7 Two-DimensionalBifurcated Duct Inlet with 30 Percent Internal Contraction

机译：具有30％内收缩的mach-2.7二维分叉管道入口性能的实验研究

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An experimental study was conducted to determine the performance of a two-dimensional, mixed-compression bifurcated duct inlet system designed for a free-stream Mach number of 2.7. Thirty percent of the supersonic area contraction occurred internally. A movable ramp was used to vary the contraction ratio for off-design operation. Boundary layer bleed regions were located on the cowl, centerbody, and sidewall surfaces. There were also provisions for vortex generators on the cowl and centerbody of the subsonic diffuser. Data were obtained over the Mach number range of 2.0 to 2.8 and at angles of yaw from 0 deg. to the maximum value prior to inlet un-start. The test at Mach 2.8 was to

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