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Source Panel Method: Normal Velocity Geometric Integral [I(ij)]

In the previous video (Flow Around an Airfoil), we ended with an expression that still needed some simplification before we could use it to solve for the source panel strengths. In this video, we go through the solution process of that term, called the geometric integral (or at least that's what I'm calling it). Don't worry, we're almost ready to code our panel method. The next video is about creating the system of equations and solving it. ===== 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...   ► Flow Around an Airfoil    • Flow Around an Airfoil: Panel Methods   ===== NOTES ===== I'll add notes here if I need to. ===== 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