Multiobjective optimization design of a compressor airfoil using evolutionary algorithms

Multiobjective aerodynamic optimization design of a compressor airfoil based on the evolutionary algorithms and Navier-Stokes solutions is developed in this paper. The maximization of the static pressure rise and minimization of the total pressure loss are taken as the design targets. The Bezier curve is applied to parameterize the designed airfoil and the corresponding control points are selected as the design variables. Aerodynamic performance of the designed airfoils is evaluated using Reynolds-averaged Navier-Stokes solution. The Baldwin-Lomax turbulence model is used. Real-coded multiobjective evolutionary algorithms are utilized to design the compressor airfoil. The Pareto solutions are obtained using the present optimization technique. Details analysis of the certain Pareto solutions and the initial design is illustrated. The feasibility of the present optimization technique is also demonstrated.