Design Of Distributed Electric Propulsion Aircraft And Research On Slipstream Effect

With the development of electric aircraft,distributed electric propulsion aircraft came into being.Engineers and researchers generally believe that this layout has the potential to greatly improve the aerodynamic efficiency of electric aircraft.In order to explore the influence of the propeller slipstream effect on the flow field of the distributed electric propulsion aircraft and tap the potential of the slipstream effect to improve the aerodynamic efficiency of the aircraft.Take a large aspect ratio electric aircraft as an example and transform it into a distributed electric propulsion aircraft.In order to provide data input for the selection and parameter matching of the distributed electric propulsion system,two high-efficiency propellers were selected and the two selected propellers were numerically simulated and wind tunnel tested.Based on the conventional electric propulsion system selection and parameter matching method,the distributed electric propulsion system selection and parameter matching method is given.Use this method to select the power system and match the parameters of the distributed electric propulsion aircraft designed in this paper.After completing the layout design of the distributed electric propulsion system,the study of the slipstream effect of the distributed electric propulsion aircraft propellers was launched.First,the prototype is numerically simulated.In order to verify the accuracy of the aerodynamic performance calculation of the complete machine,wind tunnel experiments are carried out on the scaled model of the prototype.Due to the direct grid division of the distributed electric propulsion aircraft,the number of grids will reach tens of millions.In order to reduce the amount of calculation,the equivalent disk model is used instead of the three-dimensional propeller model.Before the numerical simulation of the entire distributed electric propulsion aircraft,a set of simulation tests was carried out to verify the feasibility of the equivalent disk model to replace the three-dimensional propeller model.Then,the equivalent disk model is used to replace the three-dimensional propeller for numerical simulation,and the numerical simulation results of the aerodynamic characteristics of the distributed electric propulsion aircraft are compared with the numerical simulation results of the prototype.Finally,the flight performance of the distributed electric propulsion aircraft designed in this paper is calculated.