Hi,

1) How do I set the boundary of the computational domain to velocitygradient =0 and to static pressure at the outlet of the domain?

2) How do I create the boundary wall conditions of and aerofoil?

3) How do I find the skin friction drag of the aerofoil?

Thank You.

1) How do I set the boundary of the computational domain to velocitygradient =0 and to static pressure at the outlet of the domain?

2) How do I create the boundary wall conditions of and aerofoil?

3) How do I find the skin friction drag of the aerofoil?

Thank You.

Do you mean that you are going to simulate a 2D or 3D flow around an airfoil? If so, the shear force should be your induced drag and the total normal force will give you the total reaction force. About the boundary conditions, make an aerodynamic tube with inlet and outlet, the diameter should be 2-3 times bigger than your wing chordlength, and apply all that you need on its inlets and outlets. And, use a real wall conditions.

Regards, Basil