Study and analysis of lift to drag ratio performance of supercritical wing based on computational fluid dynamics method

Abstract

Abstract As the main airfoil of large fixed-wing aircraft at present, the supercritical wing has better performance than the traditional airfoil, especially its aerodynamic performance. Therefore, it is necessary to calculate and experiment with the supercritical wing to optimize its structure. In this paper, computational fluid dynamics (CFD) technology is used to evaluate and compare the performance of a supercritical wing (half wingspan) and a flat wing (half wingspan) with similar size and the same boundary conditions. First, shrink modelling of the two airfoils is performed using the similarity principle. Then it was imported into the simulation environment to calculate the lift-drag ratio under different boundary conditions and draw a corresponding dot plot for comparison. The results show that the aerodynamic indexes of the supercritical wing are better than those of the flat wing of the same size at the cruise stage. Under the standard cruise condition (the angle of attack of the flow is 2°, the air density is 0.5259 kg/m3, and the incoming flow velocity is 800 km/h, for example), the lift-drag ratio of the supercritical wing is increased from 15.0855 to 28.1962 by 1.869 times.