Aerodynamic Performance Of Airfoil For Unmanned Aerial Vehicles

From the successful flight of the first unmanned aerial vehicles in the beginning of the twentieth Century,the unmanned aerial vehicle has been a hot research hotspot both at home and abroad.Because of its small size,easy operation,low noise,strong concealment and many other features,it has been playing more and more important roles in the military war and people's livelihood economy and many other fields.In recent years,with the maturity of the research technology and the reducing of the research costs,unmanned aerial vehicles are gradually walking from the laboratory into the daily lives of general population.Research on unmanned aerial vehicles and airfoil aerodynamic performance,has provided theoretical foundation for improving and designing aircraft structures and creating unmanned aerial vehicles for more practical requirements.This paper has based on learning low-speed aerodynamics and computational fluid dynamics,and used CFD numerical simulation calculation method to analyze the For simplified model of the aerodynamic performance of aviation 2-D airfoil and aircraft.For the classical aviation NACA airfoils,this paper analyzed the variation rule of their lift coefficient and drag coefficient in different flow velocity and different attack angles.What is more,this paper calculated two sets of different geometric parameters of airfoils,got the influence rule of the maximum relative camber and the maximum relative thickness of airfoil in a certain range on lift coefficient and drag coefficient.For the two examples simplified models of fixed-wing unmanned aerial vehicles and quad-rotor unmanned aerial vehicle,used CFD numerical simulation calculation method and theoretical formula estimate method to analyze their respective take-off mechanism,and then compared with the parameters of the model itself,analyzed the cause of the error.