Drag Reduction Design of Transonic Airfoil Based on Particle Swarm Optimization Algorithm

Abstract

The particle swarm optimization algorithm was introduced and the six-hump camelback function problem was verified and tested. The flow field of the RAE2822 airfoil was simulated by the Navier-Stokes equation and compared with the experiment very well. Based on the aerodynamic optimization case of an airfoil, an optimization design and drag reduction design with a lift coefficient fixed were developed. In this problem, geometric constraints and aerodynamic constraints are both involved. A population of 30 individuals was generated. The CST airfoil parameterized method was used to generate the new airfoil, and the dynamic mesh technique was used to update the new mesh. The aerodynamic characteristics of each airfoil was simulated by Navier-Stokes equation and obtain the individual fitness value. A total of 20 iterations of the design were carried out. There was a strong shock wave and a large shock drag in the baseline airfoil transonic flow. The shock strength is obviously weakened after optimization. The pressure drag is obviously reduced, and the lift-drag ratio is increased by 75%.