Abstract

The effect of active flap control (AFC) on the reduction of helicopter blade-vortex interaction (BVI) noise is quantitatively analyzed in comparison with the conventional individual blade control (IBC) using a three-dimensional unsteady Euler code. This code is based on our advanced CFD code for the full configuration of helicopters. The acoustic signal of BVI noise is obtained by combining the CFD code with an acoustic code based on the Ffowcs Williams and Hawkings (FW-H) equation. As a result, it is found that AFC is quite effective for the reduction of BVI noise compared to IBC because AFC yields almost same magnitude of noise reduction as IBC with the small area of movable control surface (4.5% of IBC).

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