Aerodynamic analysis of potential use of flow control devices on helicopter rotor blades
Journal of Physics, Conference Series
Investigations of shock wave boundary layer interaction on suction side of compressor profile M Piotrowicz, P Flaszyski and P Doerffer -CFD aerodynamic analysis of nonconventional airfoil sections for very large rotor blades G Papadakis, S Voutsinas, G Sieros et al. -The origins of a wind turbine tip vortex Daniel Micallef, Busra Akay, Carlos Simão Ferreira et al. -This content was downloaded from IP address 220.127.116.11 on 25/07Abstract. The interest in the application of flow control
... flow control devices has been rising in the last years. Recently, several passive streamwise vortex generators have been analysed in a configuration of a curved wall nozzle within the framework of the UFAST project (Unsteady Effects of Shock Wave Induced Separation, 2005 -2009). Experimental and numerical results proved that the technology is effective in delaying flow separation. The numerical investigation has been extended to helicopter rotor blades in hover and forward flight applying the FLOWer solver (RANS approach) implementing the chimera overlapping grids technique and high performance computing. CFD results for hover conditions confirm that the proposed passive control method reduces the flow separation increasing the thrust over power consumption. The paper presents the numerical validation for both states of flight and the possible implementation of RVGs on helicopter rotor blades.