Abstract
Flows past helicopters have been studied using both a potential flow panel method (VSAERO) and a Navier Stokes solver, NPARC. It was found in some preliminary studies that potential method based computational fluid dynamics (CFD) could not adequately simulate the viscous flow regimes or the complex rotor wake /fuselage interactional flow, especially the low speed bluff body flows involving large scale separations. Navier-Stokes computations on a helicopter configuration with rotor have been carried out. The rotor is simulated as an actuated disc supporting a pressure jump boundary condition.
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