Wake analysis for NACA4412 in free-flight condition

Abstract: The purpose of this project is to evaluate the differences in the wake of a NACA 4412 airfoil in free-flight condition compared to wind tunnel and also investigate wall-interference. This was done using two sets of angles of attack, 5 degrees and 8 degrees. We collected data using Computational Fluid Dynamics to simulate free-flight condition and experimental data gathered from a wind tunnel, there were some key differences between these two cases. The key differences were the size of the area of high velocity deficit as well as the wake thickness and angle.