The current paper presents time-accurate numerical simulations of compressible flows past two-bladed rotor configurations using a Chimera moving grid approach.The simulations are performed for a variety of flow conditions and various blade aspect ratios.The rotor blades are rectangular,untapered and untwisted planforms.Their cross-sections are built using the NACA 0012 airfoil profile.The aerodynamic performance of the rotor is investigated using the Euler equations.The CFD- FASTRAN code was used for the computations.The pressure distributions are benchmarked against the experimental data from Caradonna and Tung.[1]and a number of previous Euler calculations by Agarwal and Deese[2]and Chen et al.[3].The comparisons indicate that the current simulations for the forward flight conditions can reproduce the pressure distributions on the blade surfaces and the prediction of shockwave locations with reasonably good accuracy.
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