PITM simulation of a turbulent flow in a plane channel with fluid injection through the lower surface [5]. Isosurfaces of instantaneous vorticity in the streamwise direction. The flow undergoes a transition process from laminar to turbulent regime. The bulk Reynolds number varies from 0 at the head end of the channel to 10^5 at the exit section. Resolution of 400 X 44 X 80 grid-points.   

 

PITM simulation of the turbulent flow over periodic hills at Reynolds number Re=37000 [15]. Vortical activity illustrated by the Q isosurfaces, Q=4.10^5/s^2. Resolution of 160 X 60 X 100 grid-points.   

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PITM simulation of a rotating channel flow [13]. Isosurfaces of vorticity modulus colored according to the pressure contours. Anticyclonic wall region: down; Cyclonic wall region: up. Bulk Reynolds number=14000, Rotation number=1.50. Resolution of 124 X 84 X 84 grid-points.   

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RSM computation of the flow around the NACA 0012 airfoil [6]. Pressure contours. Mach number = 0.779, Reynolds number=9 x 10^6. alpha =2.26 degres. Resolution of 513 X 129 grid-points.   

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RSM computation of the flow around the Aerospatial A-airfoil [6]. Pressure contours. Mach number = 0.15, Reynolds number=2.1 x 10^6. alpha =13.3 degres. Resolution of 513 X 97 grid-points.   

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Direct numerical simulation of heated turbulent channel flow [24]. Snapshot view of the scalar field in the mid-plane. Prandtl number =10. Resolution of 1024 X 512 X 1024 grid-points.   

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