Abstract
Experiments were conducted on a NACA 0012 airfoil equipped with Gurney flap. Two types of Gurney flap were used: one was solid with a height of 5% chord and the other was triangularly serrated with a height of 5% chord. The Reynolds number of the tests, ∼2 x 10 5 based on chord, was typically in the range of interest for microaerial vehicles and rotor blades of helicopters. The results confirmed the advantages of a Gurney flap, in general, and provided additional insight into their effectiveness. A simple analysis that extends the hypothesis of Liebeck on the functioning of the Gurney flap is offered
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