Comparison of an actuator disk and a blade modeling approach in Navier-Stokes calculations on the SR-3 propfan (2000)

In this paper different propeller modeling concepts are investigated that can be used in propeller-wing interaction studies. The actuator disk concept and full 3D propeller blade modeling are compared to establish the applicability of the methods for such problems. Navier-Stokes calculations have been performed on a SR-3 propfan with nacelle configuration. Two angles of incidence were considered, 0° and 4°. The actuator disk was fed with experimental and numerical data. The blade modeling calculations were performed using two different approaches: a steady state moving reference frame and a time-dependent sliding mesh approach. The actuator disk calculations seem to be capable of adequately predicting the behaviour of the propeller generated flow field at the location of a trailing wing. Blade modeling calculations deliver more detail, but are far more complex and have a severe penalty in calculation time and problem setup. Going downstream the flow field patterns of the two concepts becomes more similar which suggests the selection of the more simple actuator approach. When the flow field generated by a propfan-like propeller is used as an input for the calculation of the effects on a trailing wing, the actuator model can produce acceptable results. Symbols M Mach number k turbulence production r radial coordinate R propeller radius X streamwise coordinate (X propeller incidence angle S turbulence dissipation Q azimuth angle Copyright © 2000 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Abbreviations RNG Renormilization Group SR Single Rotation Introduction Wings on aircraft with wing-mounted propellers experience a lift distribution that is quite different from the one produced by a clean wing. The placement of the propeller has a major influence on the aircraft performance and noise production. In the numerical research on propeller-wing interaction, the model used for generation of the slipstream is of key importance (Veldhuis [1]). The wing is generally placed one or more propeller diameters behind the propeller. The vorticity originating from the blades, has been weakened and spread out by convection and diffusion, as it reaches the wing leading edge. Therefore, an accurate prediction of the local flow field around the propeller blade is generally not needed for numerical research on propeller-wing interaction. The wing experiences only the averaged, vorticity dominated flow that is produced by the propeller. When a flow around a propeller-wing configuration is calculated, there are two ways to model the propeller, that are widely used: Q Modeling the propeller as a thin actuator disk that generates a flow field that is the result of a pressure jump and a jump in tangential velocity over the disk surface. Q Full propeller blade modeling. A quasi-steady approach is appropriate when only the propeller and nacelle configuration with axi-symmetric inflow field is considered. If the propeller and wing are modeled or angle of incidence is considered, a time-dependent calculation with grid blocks, sliding relative to each other is needed.