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

A combined wing and propeller model is presented as a low-cost approach to preliminary modeling of slipstream effects on a finite wing. The wing aerodynamic model employs a numerical lifting-line method utilizing the 3D vortex lifting law along with known 2D airfoil data to predict the lift distribution across a wing for a prescribed upstream flowfield. The propeller/slipstream model uses blade element theory combined with momentum conservation equations. This model is expected to be of significant importance in the design of tail-sitter vertical take-off 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, and results compared with published experimental data.

Name thesis:degree_name

MS

Grantor dc:publisher

Brigham Young University - Provo

Author dc:creator

• Hunsaker, Douglas F.

• aerodynamic
• vertical take-off and landing
• VTOL
• SUAV
• small aircraft
• lifting line theory
• Mechanical Engineering

Language dc:language

English

Repository record dc:identifier

https://scholarsarchive.byu.edu/etd/1071

OAI identifier oai:identifier

oai:scholarsarchive.byu.edu:etd-2070