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Flow Around an Airfoil: Panel Methods

In the previous video (Building More Complex Flows), we ended with an equation for the velocity potential induced at an arbitrary point P in the flowfield, due to a uniform flow and all of the source panels that approximate our airfoil shape. In this video, we dictate a boundary condition that forces the airfoil to be a streamline of the flow, allowing us to solve for the unknowns in the velocity potential equation (all the source panel strengths). We also dictate the other boundary condition that will allow us to calculate the velocity (and thus pressure coefficient) on the airfoil surface. ===== RELEVANT VIDEOS ===== ► Panel Methods Playlist    • How To: Run XFoil from MATLAB   ► Panel Method Geometry    • Panel Method Geometry   ► Building More Complex Flows    • Building More Complex Potential Flows...   ===== NOTES ===== As shown in the text in my video at 12:32, the boundary point indices (k and k+1) are reversed. This has no implication on the derivation, but just note that the tangential vector always points from point k to point k+1. ===== ERRORS ===== If you see an error in the video, please let me know and I will include it here. ===== REFERENCES ===== Note: the links are Amazon affiliate links. If you do happen to want to buy the book and use the link below, it helps me out a little. ► Fundamentals of Aerodynamics, Anderson https://amzn.to/3emVuXU ► Foundations of Aerodynamics, Kuethe and Chow https://amzn.to/2yMg1Vi ► Theory of Wing Sections, Abbott and Doenhoff https://amzn.to/2wvZyUt