1950•NASA STI Repository (National Aeronautics and Space Administration)Requires access
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration with a Wing of 45 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfo
Robert S. Osborne
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Abstract
Memorandum presenting an investigation of a series of wing-fuselage configurations to determine the effects of wing geometry on aerodynamic characteristics. This paper presents the force, moment, wake, and downwash measurements made on a fuselage and wing-fuselage combination of specified measurements. The current phase of the investigation is focused on varying the sweepback of the 0.25-chord line of the wing.