The Kutta-Joukowski theorem states that lift is proportional to circulation. For flow around a cylinder, there are 2 stagnation points, there is also a particular value of flow circulation that moves the rear stagnation point to the trailing edge of the wing called the Kutta condition.
[[Kutta Condition]]
[[Vortex Lattice Method]] – uses the Kutta-Jukowski theorem to determine aerodynamic coefficients
Sources
- [1] “FLOW AROUND AN AIRFOIL.” Accessed: Dec. 21, 2023. [Online]. Available: https://www.av8n.com/irro/profilo_e.html
Backlinks
[[Stagnation Point]]
[[Circulation Theory of Lift]]