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Numerical Analysis of Active Flap for Noise Reduction Using Moving Overlapped Grid Method

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A three‐dimensional unsteady Euler code for the analysis of active flap control (AFC), based upon an advanced computational fluid dynamics (CFD) code for full helicopter configurations, has been developed in this study. The effect of the AFC phase angle on blade‐vortex interaction (BVI) noise is analyzed by combining the new CFD code with an acoustic code based on the Ffowcs Williams and Hawkings (FW‐H) equation for the case of a one‐bladed rotor with a stiff blade. As a result, the characteristic trend of noise intensity as a function of flap phase angle obtained by three‐dimensional CFD calculations can be explained using a classification of two‐dimensional interaction between airfoil and vortex shed from a blade with AFC. The prediction of the effect of flap phase angle by this CFD method is remarkably improved by considering the biased flow of wind tunnel. A quantitative noise reduction of 5.62 dB is obtained at the flap phase angle of 60°, where the noise signal propagates strongly almost downward for the one‐bladed rotor case.
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Document Type: Research Article

Publication date: 01 July 2007

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  • The Journal of the American Helicopter Society is the world's only scientific journal dedicated to vertical flight technology. It is a peer-reviewed technical journal published quarterly by AHS International and presents innovative papers covering the state-of-the-art in all disciplines of rotorcraft design, research and development. (Please note that AHS members receive significant discounts on articles and subscriptions.)

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