This example models and simulates the flow field around the cross section of a NACA airfoil using the inviscid potential equation. The potential field is here modeled with the classic Laplace PDE equation with a correction for the discontinuity at the trailing edge (the Kutta condition). On the boundaries, there is zero normal flow on the airfoil body, and unit velocity magnitude at the external in and out-flows of the domain.
This model is available directly in the GUI by selecting Model Examples and Tutorials… > Fluid Dynamics > Potential Flow Over an Airfoil from the File menu, and also as the MATLAB simulation m-script example ex_potential_flow1. Video and step-by-step tutorial instructions to set up and run this model are also linked below.
Moreover, this example can also be extended to perform parametric optimization in order to search for and find an optimal angle of attack. A more in-depth tutorial of this using the MATLAB scripting functionality is linked as follows.