A Numerical Vortex Approach to Aerodynamic Modeling of SUAV/VTOL Aircraft

Document Type

Conference Paper

Journal/Book Title/Conference

Rocky Mountain Space Grant Consortium Meeting Proceedings


Salt Lake City, UT

Publication Date



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.

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