A numerical lifting line method, coupled with a numerical blade element method, is presented as a low computational cost approach to modeling slipstream effects on a finite wing. This method uses a 3D vortex lifting law along with known 2D airfoil data to predict the lift distribution across a wing in the presence of a propeller slipstream. The results are of significant importance in the development of an aerodynamic modeling package for initial stages of vertical take-off and landing (VTOL) aircraft design. An overview of the algorithm is presented, and results compared with published experimental data.
A Numerical Vortex Approach to Aerodynamic Modeling of SUAV/VTOL AircraftRocky Mountain Space Grant Consortium Meeting Proceedings
Document TypeConference Paper
Citation InformationHunsaker, D. F., “A Numerical Vortex Approach to Aerodynamic Modeling of SUAV/VTOL Aircraft,” Rocky Mountain Space Grant Consortium Meeting Proceedings, Salt Lake City, Utah, May 2006.