返回Google圖書搜尋

Langley Full-scale-tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid-cooled Engine

出版	National Advisory Committee for Aeronautics, 1946
URL	http://books.google.com.hk/books?id=vXM4CFElt8oC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋An investigation has been made in the Langley full-scale tunnel to determine the thickness and shape of profile of the boundary layer on the fuselage of a typical monoplane fighter airplane with a single liquid-cooled engine. The results showed that, for the range of angles of attack and fuselage stations investigated, the maximum displacement thickness was nearly 1.2 inches and was at the most rearward station (81.6 percent of the fuselage length). The displacement thickness was found to be greatly affected by the pressure gradients over the windshield-canopy combination and in the wing-fuselage juncture. An average value for the shape parameter between 1.3 and 1.4 was obtained for the turbulent boundary layer.