Abstract
This chapter presents CFD results for the performance of the W3 Sokol rotor in forward flight and an investigation of the potential effect of the implementation of an active Gurney. Rigid and elastic blade models were considered and calculations were guided using flight test data. The Gurney flap was extended from 40 %R to 65 %R and was located at the trailing edge of the blade. The size of the Gurney was selected to be 2 % of the chord based on previous chapter for the same rotor in hover. All results were trimmed to the same thrust as flight tests. The harmonic analysis of the flight test data proved to be a useful tool for identifying vibrations on the rotor caused by stall at the retreating side, and a carefully designed Gurney flap and actuation schedule were essential to alleviate the effects of flow separation.
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