The aerodynamic performance of a two-element airfoil with a 90 deg. trailing edge flap was experimentally investigated. The 5 percent-chord long flap, significantly increased the lift of the baseline airfoil, throughout a wide range of angles of attack. The maximum lift coefficient of the flapped wing increased too, whereas the lift/drag ratio decreased.
Issue Section:Technical Briefs
Topics:Aerodynamics, Airfoils, Chords (Trusses), Drag (Fluid dynamics), Wings
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