Implementation of a Method to Determine Aerodynamic Propeller-Wing Interaction

The scalability and lightweight design of electric motors within (hybrid-) electric propulsion systems facilitates the distribution of propulsion. The aerodynamic interaction of a swirling propeller slipstream and a lifting surface can be beneficial regarding a vehicle’s propulsive efficiency. This report presents the implementation of a numerical method of low computational effort based on Blade Element Momentum Theory combined with a Vortex Lattice Method using a simple slipstream model. Goal of the method is to determine basic effects and trends of such aerodynamic interaction effects for conducting design studies regarding principle parameters of propeller-wing tractor configurations. The implementation is depicted and a verification is given with experimental results from literature.