A three-dimensional, unsteady Navier-Stokes numerical methodology to calculate economically and accurately the flow field of multi-bladed helicopter rotor and fuselage in hover and forward flight will be developed. Ad hoc wake models will not be used to model the vortex wake; instead, the complete vortical wake will be captured as a part of the overall flow field solution. A Navier-Stokes upwind scheme will be used in conjunction with a Chimera grid for preserving and convecting concentrated vortices. Phase I will demonstrate a calculation for a rotor-body combination in hover which would provide a solid foundation for realistic calculations in hover and forward flight in Phase II. The individual items to be completed in Phase I are the gridding of a two-bladed rotor and fuselage for a Chimera scheme; implementation of Chimera and Pegasus schemes into the Navier-Stokes numerical method; and a demonstration calculation of rotor-body flow in hover and comparing the results with experiments.Commercial applications include the design of advanced technology helicopters with efficient aerodynamics and aeroacoustics performance, including the selection process of rotor blade shapes and planforms and the interaction of multiple moving bodies relative to each other such as the main rotor and tail rotor and engine turbines and compressors.viscous flow, Navier-Stokes equations, unsteady, hover, forward flight, helicopter rotor, wake, interaction flow, transonic, three-dimensionsSTATUS: Phase I Only
