A Numerical Vortex Approach to Aerodynamic Modeling of SUAV/VTOL Aircraft
Rocky Mountain Space Grant Consortium Meeting Proceedings
Salt Lake City, UT
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.
Hunsaker, 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.
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