Kutta and wake conditions over an airfoil
I will be very grateful for you for any help.
The Grid generation which I building orthogonal C- type, according the below Ref. 1-Nearly Orthogonal Two-Dimensional Grid Generation with Aspect Ratio Control. J. Comp. Phys. 171, 2001. 2- 2D orthogonal grid generation with boundary point distribution control, J. Comput. Phys. 125, 440-453, 1996). Then, I reached to a good structure orthogonal C-Type grid generation about airfoil.
Now, my problems are related to the solution of the 2D potential, Incomp. subsonic flow on airfoil more specific at trailing edge and also when give angle of attack for potential flow. I used finite difference nunmerical method with SOR to Solution Laplace equation of perturbation velocity potential.
My question!!!!!!! ------------------- __________________________________________________ ________ I cant understand how applied the Kutta Condition on trailing edge and the boundary condition on wake surface. and also I need the finite difference representation of Kutta and wake boundary condition.
__________________________________________________ __ Thanks for any suggestion or opinion, with my best regards. .
Laith Mohammed Jasim Laith20042001@yahoo.com
Kutta condition - Naca 0012
I'm solving the flow around Naca 0012, in control volume. My questionis is how to implement the kutta condition practically. I know exactly what this condition means, but I realy don't know how to implement. Can anyone help me with this?
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