Coupled Viscous Vortex Particle Method and Unstructured CFD Solver for Rotorcraft Aerodynamic Interaction Modeling

The rotorcraft aerodynamic interaction is a complicated problem and remains an extremely challenging aspect of rotorcraft analysis. This STTR is dedicated to developing a solution for the complicated rotorcraft aerodynamic interaction problem. The Phase I research coupled a state-of-the-art vortex particle method (VPM) with an unstructured Navier-Stokes CFD body surface solver and prototyped a hybrid solver for the complicated rotor/fuselage interaction problem. The hybrid solver successfully demonstrated an accurate solution for the prediction of the unsteady flow field of the rotor wake and the unsteady pressure over the fuselage surface due to the interacting rotor wake effect. Phase II will aim at a full development of the methodology and emphasize the application of the advanced hybrid tool for solving the complicated rotorcraft aerodynamic interaction problems. Phase II will further enhance the methodology, develop a standard flow solver coupling utility, and fully implement the hybrid methodology. Phase II will also evaluate the hybrid solution and compare the results with wind tunnel and flight test measurements to substantiate the hybrid modeling and analysis tool.