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Results of boundary layer transition tests of the 0.025-scale right-hand wing and truncated aft fuselage model (94-0) in the AEDC VKF B hypersonic wind tunnel (QH90A, MA29)

机译：aEDC VKF B高超音速风洞（QH90a，ma29）中0.025比例右翼和截尾后机身模型（94-0）的边界层过渡试验结果

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作者
Foust, J. W.;
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年度 1979
页码 1-1214
总页数 1214
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
BOUNDARY LAYER TRANSITION; FLIGHT SIMULATION; SPACE SHUTTLE ORBITERS; WIND TUNNEL TESTS; GRAPHS (CHARTS); HYPERSONIC SPEED; REENTRY; SPACECRAFT CONFIGURATIONS; TABLES (DATA);

机译：边界层转换;飞行模拟; spaCE sHUTTLE ORBITERs;风洞隧道测试;图表（图表）;超速的;再入;航天器配置;表（数据）;

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2. Hypersonic Wind-Tunnel Measurements of Boundary-Layer Transition on a Slender Cone [J] . Casper Katya M., Beresh Steven J., Henfling John F., AIAA Journal . 2016,第4期

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5. Development and testing of a new optimum design code for hypersonic wind tunnel nozzles, including boundary layer, turbulence, and real gas effects. [D] . Tolle, Ralph Charles. 1995

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8. Results of tests on a 0.04 scale Space Shuttle Orbiter forebody model (83-0) in the AEDC VKF hypersonic wind tunnel B to obtain aerodynamic heating distribution on lower fuselage and RCS nozzle area (OH103A) [R] . Lemoine, P. L., Nakamoto, J. R. 1982

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Results of boundary layer transition tests of the 0.025-scale right-hand wing and truncated aft fuselage model (94-0) in the AEDC VKF B hypersonic wind tunnel (QH90A, MA29)

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