Graphical representation of the NACA 0012 uncambered section under study.
Streamlines plotted of the numerical solution of the flow field over the airfoil.
Comparison of lift results from numerical analysis and experimental data.
This plot shows the predicted and experimental pressure distributions over the airfoil.
Experimental report.
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MATLAB code.
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NACA 0012 Airfoil Analysis and Testing
This investigation of a NACA 0012 airfoil section used a numerical vortex-lattice method to predict the aerodynamic behavior of the airfoil with original MATLAB code. Numerical solutions were predicted and compared to experimental results.
This project was completed as an assignment for MECHENG 712 Aerohydronamics, University of Auckland.
