Study on optimization method for airfoil in supersonic case based on Particle Swarm optimization(PSO)

Abstract

In order to adapt to the society demand of requiring faster aircraft, this thesis aims at combining Particle Swarm optimization (PSO) with Computational Fluid Dynamics (CFD) to get a optimized airfoil which possesses a better areodynmics performance in supersonic case. This paper adopts the method of using small disturbance equation to simulate the flow field, which is more effective and stable and easier to implement. Besides, this paper adopts traditional PSO. The results show that the magnitude of ratio of lift-drag has increased by 16.29% and the magnitude of lift has risen by 13.69%, while the magnitude of drag has decreased by 2.2% after the optimization, compared with the initial airfoil. Besides, the results also reveal that the front of the optimized airfoil is wider than that of the initial airfoil and the rear of the optimized airfoil is narrower than that of the initial airfoil, which can represent that the optimized airfoil effectively enlarge the magnitude of ratio of lift-drag and lift and suppresses the drag and influence generated by shock.