elib (German Aerospace Center) · 2005 · 11 citations · 0 references
EngineeringAerospace EngineeringMechanical EngineeringAerodynamicsComputational Fluid DynamicsFluid DynamicsComputational AerodynamicsExperimental AerodynamicsExternal AerodynamicsRotorcraft AerodynamicsUnsteady AerodynamicsWind-tunnel TestingBlade AerodynamicsComputational Unsteady AerodynamicsElasticityForward Flight AerodynamicsMach NumberNavier-stokes SolversRotor AerodynamicsRotor Blade Aerodynamics
Air flow past a reduced scale model of an Eurocopter BO-105 fuselage-main-rotor-tail rotor configuration was simulated by solving the time dependent Navier-Stokes equations. The computations correspond to wind tunnel measurements carried out under Mach 0.1578 forward flight conditions. Main and tail rotors' blades were considered rigid in the computations, and their motions were achieved by a moving overlapping grid technique (Chimera). The numerical results are judged against unsteady pressure measured on the fuselage and the blades. Apart from blade elasticity effects, good agreement with experiment was found.