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Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles

出版	National Advisory Committee for Aeronautics, 1949
URL	http://books.google.com.hk/books?id=yQYVj06p4WUC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋The results of tests of 11 triangular wings were conducted at Mach numbers 1.62, 1.92, and 2.40 to determine the effect of leading-edge shape and to compare actual test values with the nonviscous linear theory. The two series of wings had identical plan forms, a constant thickness ratio of 8 percent, a constant location of maximum-thickness point of 18 percent, and a range of apex half-angles from 10 to 45 degrees. The first series had an elliptical leading edge and the second series, a wedge leading edge. Measurements were made of lift, drag, pitching moment, and pressure distribution, the latter being confined to three wings at one Mach number.