The Aerodynamic Optimization Of Wing Under The Influence Of Propeller Slipstream

Since the emergence of propeller aircraft,it is active in the aviation field because of its low fuel consumption and high reliability.During the flight of propeller aircraft,the influence of propeller slipstream on the wing cannot be ignored.In this paper,some aerodynamic analysis and optimization of the wing under the influence of propeller slipstream are carried out as follows:1)Aerodynamic analysis of wing under the influence of propeller slipstreamThe momentum source method based on the blade element theory is used to simulate the propeller slip flow,and the flow field of the wing model is numerically simulated.The aerodynamic interference of the propeller on the wing is analyzed,and the curve of the lift-drag coefficient with the angle of attack is obtained.The results show that compared with the flow field without propeller,the lift coefficient and drag coefficient of the wing are increased by the propeller slip flow,and the curves of them change with the angle of attack have the same trend.2)The aerodynamic optimization of wing under the influence of propeller slipstreamAerodynamic optimization of wings for increasing lift-to-drag ratio is studied under cruise condition with propeller slipstream.According to the different influence of propeller slip flow on the wing at different stations,that is,the boundary conditions are different,the wing is divided into the inner and outer sections,and the representative section airfoils of the two sections of the wing are selected respectively.Two working conditions are used to optimize:working condition 1 is that the two section airfoils only consider the effect of propeller slip flow,and do not consider the influence of flow field;Working condition 2 is that the inner wing section airfoil is affected by the propeller slip flow and flow field,and the outer wing section airfoil only considers the influence of flow field.Then,the parametric modeling of airfoil is carried out by CST method to determine the control parameters.By optimizing Latin hypercube design to extract sample points,Kriging surrogate model is established,and multi-island genetic algorithm is used as optimization algorithm.The momentum source method is used to simulate the flow field of propeller.Under the two conditions,the optimized airfoil is generated by using the optimized control parameters as the benchmark,and the wing is formed for aerodynamic analysis.The calculation results show that compared with the original wing,the lift-drag ratio increases by 9.98%and 10.95%,respectively.