Effects of Distributed Propellers Slipstream on Aerodynamic Characteristics of Wing

Distributed electric propulsion is a new concept in recent years. It makes full use of the scale-free nature of electric energy and distributes multiple propulsion devices on the wings or fuselage to improve the aerodynamic performance of aircraft. This study will analysis the effect of distributed propellers slipstream on aerodynamic characteristics of the wing. The study will analysis the propeller-wing system by means of momentum theory, actuator disk model and CFD method to explore the high-lift mechanism of the distributed propeller slipstream. Based on the momentum theory, a method to analyze the lift coefficient of the wing is proposed by using the velocity of the slipstream behind the propellers. Based on the actuator disk model, the influence of different number of propellers on the lift coefficient and lift coefficient distribution of the wing was investigated by OpenVSP. Based on CFD method, calculation and simulation were carried out through Fluent, and k-omega SST model was used to analyze the interaction of the propeller-wing system. The research results show that the distributed propeller slipstream will not only increase the airflow speed over the wing, the rotation of the slipstream also has a great influence on the wing. In addition, the smooth flow of wingtip vortex offset also has great effect on aerodynamic characteristics of the wing.