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A Numerical Blade Element Approach to Estimating Propeller Flowfields
45th AIAA Aerospace Sciences Meeting and Exhibit
  • Doug F. Hunsaker, Utah State University
Document Type
Conference Paper
Publisher
American Institute of Aeronautics and Astronautics
Location
Reno, NV
Publication Date
1-8-2007
Abstract
A numerical method is presented as a low computational cost approach to modeling an induced propeller flowfield. This method uses blade element theory coupled with momentum equations to predict the axial and tangential velocities within the slipstream of the propeller, without the small angle approximation assumption common to most propeller models. The approach is of significant importance in the design of tail-sitter vertical takeoff and landing (VTOL) aircraft, where the propeller slipstream is the primary source of air flow past the wings in some flight conditions. The algorithm is presented, the model is characterized, and the results (including the results of coupling the propeller model with a lifting-line aerodynamic model) are compared with published experimental data.
Citation Information
Hunsaker, D. F., “A Numerical Blade Element Approach to Estimating Propeller Flowfields,” 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, Jan. 8-11, 2007, AIAA-2007-374.