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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 having a wing of 60 degree sweepback, aspect-ratio 4, taper ratio 0.6, and NACA 65A006 airf

Raymond B Wood, Frank F Fleming

Abstract

Report presenting a study of the effect of sweep on wings with the NACA 65A006 airfoil section in the 8-foot high-speed tunnel. This particular investigation included a wing with that airfoil section, 60 degrees of sweepback at the quarter chord, an aspect ratio of 4, and a taper ratio of 0.6. Results regarding force and moment characteristics and wake and downwash characteristics are provided.

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Available abstract

Key concepts: Airfoil, Wing, Downwash, Chord (peer-to-peer), Mach number, Transonic, Wing twist, Fuselage