A Physics-Based Investigation Of Gurney Flaps For Rotor Vibration Reduction

A dynamically deployed Gurney flap was examined as a vibration reduction mechanism. A NavierStokes/Free wake hybrid method was used for a physics-based investigation of the Gurney flap effect. A previously trimmed prescribed motion was used for a quick examination of this concept. The 4-perrevolution normal force at the hub was compared with the loads for a higher harmonic controlled rotor and the baseline rotor. The simulation showed that the proper Gurney flap deployment reduced 80% of the 4P normal force vibration, whereas the higher harmonic controlled rotor reduced 53%. With proper on-board controller, further reduction of the vibration is expected with the Gurney flap. However, the Gurney flap caused blade sectional nose-down pitching moment and altered the trim condition. Thus, additional CFDCSD coupling analysis for aeroelastic deformation and rotor trim is required. This record was migrated from the OpenDepot repository service in June, 2017 before shutting down.