Study dealing with design of efficient wings for supersonic aircraft used wings having sweepback of 50° at quarter-chord line, taper ratio of 0.20, NACA 65A005 thickness distribution, and aspect ratio of 3.5; tests were made at Reynolds number ranging from 1.2×106 to 3.6×106 through angle of attack range of -20 to 20°; analysis and comparison with theory presented.
Effects at mach numbers of 1.61 and 2.01 of camber and twist on aerodynamic characteristics of three swept wings having same planform
NASA -- Tech Note
1961
48 pages
Report
English
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