Hi Anyone may tell me abt Kutta Condition in CFD. Thnx

it means that the difference pressure at two sides in TE should be zero!

Do u mean pressure side and suction side? Trailing edge is a line not a face so how it is possible to have two sides?

If I remember correctly, the Kutta condition states that the rearward stagnation point on an airfoil must coincide with its trailing edge, which is dictated by the action of viscosity. Without viscosity, you could not produce any lift, and the velocity and pressure gradients around the trailing edge would be directly proportional to its 'sharpness'. In potential flow solvers, which lack viscosity, the Kutta condition needs to be imposed by adding just the right amount of circulation to the solution. In Euler and Navier-Stokes solutions, the Kutta condition is automatically satisfied due to the presence of numerical or physical viscosity.