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Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities

Dean R. ChapmanWilliam R. WimbrowRobert H. Kester

出版	National Advisory Committee for Aeronautics, 1952
URL	http://books.google.com.hk/books?id=5NVCAQAAIAAJ&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋

The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.