Aspects Regarding Airplane Propeller Flow Field Mathematical Model

This paper deals with the aerodynamic considerations of propeller design. The optimum blade loading was prescribed according to the condition that requires the trailing vortex system to lie along a helical surface in the ultimate wake. The flow field mathematical model was based on the general theory of the propeller, applied either to free propeller or shrouded one. The equation for induced velocity was solved numerical with Maple soft and the CFD results were obtained in Fluent environment. The velocity field and streamlines show a good behavior of the propeller for a large interval of flight speed and propeller rotational velocity. As compared to the airplane wing, in the case of a propeller blade the induced velocity is concentrated in a more limited area as the diameter of a propeller is smaller than the span of an airplane wing. The pitch to diameter ratio and advanced ratio correspond to a propeller with tow blades and an elliptic platform shape.