Print Email Facebook Twitter The Behaviour and Performance of Leading Edge Vortex Flaps Title The Behaviour and Performance of Leading Edge Vortex Flaps Author Ellis, D.G. Institution Cranfield Institute of Technology, College of Aeronautics, Department of Aerodynamics Date 1986-02-28 Abstract Subsonic wind tunnel tests were conducted on a series of leading edge vortex flaps to determine the improvements in lift/drag ratio that were possible. Various flap sizes and deflection angles were investigated. Trailing edge flap effects on leading edge vortex flap behaviour were also studied. Lift/drag ratio improvements of more than 20% were found at moderate angles of attack. The results clearly indicate that the vortex flap can improve the efficiency of slender wings when operating in an aerodynamic environment governed by leadii g edge separation and vortex flow. Starting in 1946 as the College of Aeronautics, the Cranfield Institute of Technology was granted university status in 1969. In 1993 it changed its name to Cranfield University. To reference this document use: http://resolver.tudelft.nl/uuid:3222026e-29ef-4af8-90cc-bbc5d3ccc2d6 Publisher Cranfield Institute of Technology Source College of Aeronautics Report 8601 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1986 Cranfield Institute of Technology Files PDF Cranfield_College_of_Aero ... 1-1986.pdf 58.35 MB Close viewer /islandora/object/uuid:3222026e-29ef-4af8-90cc-bbc5d3ccc2d6/datastream/OBJ/view