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Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9
Harold MirelsJames M. Jagger
其他書名
Wing tip with subsonic trailing edge
出版National Advisory Committee for Aeronautics, 1949
URLhttp://books.google.com.hk/books?id=mwVv0vfyEwkC&hl=&source=gbs_api
EBookFULL_PUBLIC_DOMAIN
註釋An investigation was conducted at a Mach number of 1.91 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic leading edge swept back at 70 degrees. Except for pressure distribution on the top surface in the immediate vicinity of the subsonic leading edge, the maximum difference between linearized theory and experimental data was 2 1/2 percent (of free-stream dynamic pressure) for angles of attack up to 4 degrees and 7 percent for angles of attack up to 8 degrees. Pressures on the top surface nearest the subsonic edge indicated local expansions beyond values predicted by linearized theory.