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Investigation at a Mach Number of 1.2 of Two 45 Degree Sweptback Wings Utilizing NACA 2-006 and NACA 65A006 Airfoil Sections

Homer B Wilson

Abstract

Report presenting an investigation in the low-turbulence pressure tunnel at Mach number 1.2 to determine lift, drag, and moment characteristics of a wing with an airfoil section designed for maximum lift at low speeds, 45 degrees of sweepback, aspect ratio 4, and taper ratio 0.6. A similar wing with the NACA 65A006 airfoil section was also investigated and compared to the experimental wing.

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Available abstract

Key concepts: Airfoil, NACA airfoil, Drag divergence Mach number, Wing, Mach number, Lift-induced drag, Lift-to-drag ratio, Lift (data mining)