Abstract
The dynamic stall behavior of an OA209 rotorcraft airfoil is examined under the influence of a varying incident velocity. Therefore, a harmonic flow velocity variation is added to the pitch motion of the airfoil in antiphase. Results from two-dimensional unsteady RANS computations are presented for steady and periodic flow velocity. The unsteady flow velocity in the computational domain is generated by a fore-aft motion of the airfoil. Both methods are approximations of the flow conditions a blade section of a helicopter rotor experiences during fast forward flight. Finally, the numerical predicted aerodynamic coefficients are used to investigate the modeling capabilities of semi-empirical formulations for a simultaneous angle of attack and incident velocity change.
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Acknowledgments
The present investigations were partly funded in the framework of the LuFo IV project ECO-HC2. The authors would like to thank the Loads and Flight Mechanics department of Airbus Helicopters for the excellent collaboration.
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Schicker, D., Hajek, M. (2016). Influence of Periodically Varying Incident Velocity on the Application of Semi-Empirical Dynamic Stall Models. In: Dillmann, A., Heller, G., Krämer, E., Wagner, C., Breitsamter, C. (eds) New Results in Numerical and Experimental Fluid Mechanics X. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 132. Springer, Cham. https://doi.org/10.1007/978-3-319-27279-5_31
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DOI: https://doi.org/10.1007/978-3-319-27279-5_31
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