GURNEY FLAP INFLUENCE ON NACA 1410 AIRFOIL
Abstract
This paper presents a study of a Gurney flap on the trailing edge of a NACA 1410 profile for different angles of attack and variable geometries. The generic model was created in Catia v5 R21 and imported for CFD simulation in ANSYS Fluent. The Gurney flap model simulation covers variables angles of attack from 00 to 100 with an inlet velocity of 51.5 m/s and Reynolds number of 3.5x106. The CFD results for lift and drag were shown for two different Gurney flap heights. Based on these CFD results for the model the lift increases with angle of attack and Gurney height until the maximum point at with the stall occurs. This point at which the maximum lift occurs varies depending of the configuration used.
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