In this sample geometry is much simpler, but physics is more complicated – this is the problem of calculating turbulent flows with severe velocity gradients.
Particle paths for upper wing surface were calculated for increasing freestream Mach number - 0.8, 0.85, 0.9, 0.95 М (i.e. transonic velocity close to sonic was investigated).
The solution required 3D-grid of approximately 170,000 points separated on 4 partially overlapping zones.
The two zones immediately above and below the wing have a fine grid in the normal direction. In these two zones, the thin layer Navier-Stocks equations were solved.
In the two zones, away from the wing the flow was assumed inviscid and governed by the Euler equations.
The zones are connected by locally interpolating the overlap region, typically two cells.