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Google圖書搜尋
Effects of Sweep and Angle of Attack on Boundary-layer Transition on Wings at Mach Number 4.04
Robert W. Dunning
Edward F. Ulmann
出版
National Advisory Committee for Aeronautics
, 1955
URL
http://books.google.com.hk/books?id=wMpCAQAAIAAJ&hl=&source=gbs_api
註釋
Wind-tunnel tests were conducted at a Mach nmnber of 4.04 to determine the effects of leading-edge sweep, angle of attack, and leading-edge thiclmess on boundary-layer transition on flat-plate wings. In addition, some results were obtained on wings having rounded leading edges. The transition point was determined for angles of attack up to 20 degrees and for leading-edge sweep angles frcm 0 to 72 degrees by the luminescent-lacquer technique of bouudary-layer visualization.
