AERODYNAMIC ANALYSIS OF NACA 6409 AIRFOIL IN WIND TURBINE BY USING PANEL METHOD

Abstract

This article presents the theoretical basis and applicability of XFLR5 code to conduct aerodynamic analysis of wind turbine airfoil model NACA 6409 at low Reynolds numerical values. The new XFLR5 code is developed based on XFOIL code, which is very popularly used in the field of wing design in the world. The mathematical foundations of XFLR5 include Lifting Line Theory (LLT), Vortex Lattice Method (VLM) and Panel Method (PM). In this study, the PM method will be used to analyze aerodynamic parameters such as lift coefficient C_l, drag coefficient C_d,  factor C_l/C_d and pressure coefficient C_p placed on the surface of the NACA 6409 wing sample when operating at different angles of attack. The PM method has a fast analysis time and the obtained results show good agreement with previously published experimental data.