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Separation Ahead of Controls on Swept Wings
Kaufman Louis G. (II)L. Michael Freeman
出版Aeronautical Research Laboratories, Air Force Systems Command, 1975
URLhttp://books.google.com.hk/books?id=vzSZ0rsQHeUC&hl=&source=gbs_api
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註釋Shock-induced flow-separation ahead of trailing edge controls on swept wings is investigated with emphasis on the effects of boundary layer transition on the location and shape of the separation line. Experimental results were obtained by using forward facing steps mounted on swept-leading-edge flat-plate wing models in the ARL Mach 6 Tunnel for model running length Reynolds numbers varying from 0.9 to 33 million. The data support qualitatively a proposed, strip-type method for estimating, the extent and shape of the three dimensional region of separated flow ahead of controls on swept wings. (Author).