OPTIMASI AIRFOIL MENGGUNAKAN PARTICLE SWARM DENGAN PARAMETERISASI CST CLASS SHAPE TRANSFORMATION
Airfoil is a cross sectional profile that applied to the transport vehicle and energy generation as a cross section of the turbine blade. Airfoil designed is expected to produce maximum lift, but drag to a minimum. The purpose of this study were 1) Aerodynamics validation of panel method with ViscousInviscid Interaction; 2) Analysis the aerodynamic airfoil lift and drag coefficients; 3) Applying Particle Swarm Optimization to get the geometry airfoils that provide lift and drag coefficient ratio maximum (CL/CD max) The first phase to determines the airfoil profile using a Class Shape Transformation (CST) Airfoil will be analyzed using the panel method and applied flow model in singularity of source and doublet. The solution from panel method is a condition that is to be viscous flow. If the angle of attack is high enough solution obtained with this approach is no longer accurate. To improve the results is applied a viscous inviscid interaction method of quasi simultaneously. This process is repeated until convergence. By using Particle Swarm Optimization will be obtained airfoil profile with a maximum coefficient of lift and drag. However, if the optimization procedure is not optimal, it will be updated geometry, to obtain convergence. Conclusions of research are: 1) The panel methods with ViscousInviscid Interaction gives good results and accurate, with an average error below 9.5% 2) The greater the value of the Reynolds number, value of maximum CL/CD will be higher; 3) The maximum thickness and camber tends to increase with an increase in the Reynolds number; 4) Optimization of CST airfoil with Particle Swarm gives best results. This is because the global optimum solution added another iteration to obtain the best of the best solutions.