A TRANSONIC-WING INVESTIGATION IN THE LANGLEY 8-FOOT HIGH-SPEED TUNNEL AT HIGH SUBSONIC MACH NUMBERSnAND AT A MACH NUMBER OF 1.2 WING-FUSELAGE CONFIGURATION WITH A WING OF 45° SWEEPBACK, ASPECT RATIO 4, TAPER RATIO 0.6, AND NACA 65A006 AIRFOIL SECTION

摘要

As part of an NACA research program, an investigation of a series of wing-fuselage configurations is being conducted in the Langley 8-foot high-speed tunnel to determine effects of wing geometry on aerodynamic characteristics. In the first part of this investigation, force, moment, wake, and downwash measurements were made on a fuselage and a wing-fuselage combination employing a wing with 45° sweepback of the 0.25-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65AOO6 airfoil section parallel to the plane of symmetry at Mach numbers from 0.60 to O.96 and at a Mach number of 1.2. The results are presented in this paper.