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Flow control with the aim to avoid or at least delay flow separation and thus enhance performance of rotorcraft has been a topic in various recent investigations. Increase of maximum lift combined with drag reduction in steady applications as well as improvements of lift-, drag- and pitching moment cycles in dynamic stall problems on rotor blades are of major concern. In the present study a time accurate 2D RANS solver has been modified to enable a variety of boundary conditions for the simulation of flow control problems. With rather simple code modifications it is shown that complex control devices like synthetic jet control, running belt (wall movement) or representation of special surface materials can be taken into account in a simple and straightforward manner. Systematic calculations have shown the efficiency of the present code modifications. A common turbulence model, the Spalart/Allmaras one equation model, has been used. In addition a transition model can be taken into account as well. The numerical calculations have been compared with corresponding experimental data where available. |
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