1955•NASA STI Repository (National Aeronautics and Space Administration)Requires access
The Effect of Leading-edge Droop upon the Pressure Distribution and Aerodynamic Loading Characteristics of a 45 Degree Sweptback Wing at Transonic Speeds
James W Schmeer
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Abstract
Report presenting an investigation in the 16-foot transonic tunnel to determine the effects of leading-edge droop on the pressure distribution on a 45 degree sweptback wing with an aspect ratio of 4, a taper ratio of 0.6, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the chordwise pressure distributions, wing-panel characteristics, wing-section characteristics, and maximum additional normal load on wing leading edge are provided.