Boundary condition for solid body motion in "still" air
for a case of "static" wing in a "moving air", which is incompressible, the boundary condition like velocity inlet (for incoming flow), outflow (for outlet) are ok.
But if the wing is itself doing unsteady motion like flapping or sweeping (defined by some udf) in a "still" air, then how the boundary conditions are given at inlet and outlet. (considering that the wing is moving with a velocity that corresponds to incompressable flow).
What boundary conditions can be given in the front, in the rear, top and bottom of the complete O-type domain.
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