Uploaded May 2020 | Updated September 2026, 2 weeks ago

---

In this video, we will combine the source panel method and vortex panel method into a hybrid source/vortex panel method that is more robust than our previous vortex panel method implementation, and which follows the method of Hess and Smith. In the next video, we will implement the equations shown here in the MATLAB and Python code.

===== RELEVANT VIDEOS =====
► Panel Methods Playlist
youtube.com/watch?v=bWjo3N9COz4&list=PLxT-itJ3HGuUDVMuWKBxyoY8Dm9O9qstP

► I(ij) Geometric Integral Derivation
youtube.com/watch?v=76vPudNET6U

► J(ij) Geometric Integral Derivation
youtube.com/watch?v=JRHnOsueic8

► Mx(pj) and My(pj) Geometric Integral Derivation
youtube.com/watch?v=BnPZjGCatcg

► K(ij) Geometric Integral Derivation
youtube.com/watch?v=5lmIv2CUpoc

► L(ij) Geometric Integral Derivation
youtube.com/watch?v=IxWJzwIG_gY

► Nx(pj) and Ny(pj) Geometric Integral Derivation
youtube.com/watch?v=TBwBnW87hso

► Source Panel Method: Airfoil
youtube.com/watch?v=fdNOYdwY9Bw

► Vortex Panel Method: Airfoil
youtube.com/watch?v=JL2fz-xTTT0

===== NOTES =====
- On the whiteboard at 13:55 (and on), the final term on the RHS (b array) has a beta_N, which for this 3-panel problem, can just be written as beta_3.

===== 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
amzn.to/3emVuXU
► Foundations of Aerodynamics, Kuethe and Chow
amzn.to/2yMg1Vi
► Theory of Wing Sections, Abbott and Doenhoff
amzn.to/2wvZyUt