首页> 美国政府科技报告 >A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

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A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

机译：Langley 8英尺高速隧道中的跨音速翼探测，高亚音速马赫数和马赫数1.2。：机翼 - 机身配置，具有0度后掠翼，纵横比4.0，锥度比0.6和NaCa 65a006 ai

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作者
Cahn, Maurice S; Bryan, Carroll R;
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年度 1951
页码 1-39
总页数 39
原文格式 PDF
正文语种 eng
中图分类工业技术;
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2. Force Measurements on a Body wing tail configuration (KaHa Model) at Mach numbers of 0.4 , 0.6 and 0.8 and incidences from 30° to 65° [O] . Kanagarajan V, Hartmann K 1988

机译：马赫数为0.4，0.6和0.8且入射角为30°至65°的机翼尾翼构型（KaHa模型）上的力测量

A transonic-wing investigation in the Langley 8-foot high-speed tunnel at high subsonic Mach numbers and at a Mach number of 1.2. : wing-fuselage configuration having a wing of 0 degrees sweepback, aspect ratio 4.0,taper ratio 0.6, and NACA 65A006 ai

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