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Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 60 Degrees, Aspect Ratio 2, Taper Ratio 0.6, and NACA 65A006 Airfoil Section : Transonic Bump Method

Boyd C Myers, Thomas J. King

Abstract

From Introduction: This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream.

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Available abstract

Key concepts: Airfoil, Chord (peer-to-peer), Wing, Fuselage, Aerodynamics, Lift-to-drag ratio, Aspect ratio (aeronautics), NACA airfoil