Projects
FLOWer
The CFD-tool FLOWer solves the compressible Reynolds-averaged
Navier-Stokes equations on block structured grids. It is optimized
for the simulation of exterior flows in the subsonic, transonic
and supersonic flow regime. FLOWer is developed by the German
Aerospace Center DLR with contributions from several German
universities. The code is intensively used by the German aerospace
industry.
FLOWer is based upon a finite volume discretization. Several
central and upwind schemes are available. Turbulence can be
modeled with algebraic, one or two equation models or Reynolds
stress models. The time integration can be performed with
explicit or implicit methods. The time integration of the
flow equations is performed with an explicit multi-stage scheme
and multi grid acceleration whereas the turbulence equations
are solved with an implicit DDADI-method. For time accurate
simulations an implicit dual time stepping method is available.
FLOWer can handle meshes with hanging nodes, grid overlap
(Chimera) and moving/deforming meshes. For shape optimization,
an inverse design option and an adjoint method is available.
The flow solver is parallelized based on MPI and is optimized
for vector computers.
Example of high performance computing with FLOWer
The prediction of the flow field around a helicopter is
challenging for any CFD method. Various flow phenomena including
boundary layers, flow separations, vortices and widely disparate
velocities must be considered. The capabilities of FLOWer
are demonstrated by a simulation of the unsteady flow around
a BO105 helicopter wind tunnel model including the model support
strut. The computational mesh was created by using the overlapping
grid approach. This method accounts for the moving blades
and allows simplification of the mesh generation. The total
grid system consists of 11.7 million grid cells. The computation
of the unsteady flow took four weeks using eight processors
of the NEC SX6 vector computer. The results presented in the
figures show the pressure distribution on the body surface
and the vortices in the flow field.
Contact
Dr. Martin Galle
NEC High Performance Computing Europe
European HPC Technology Center,
Stuttgart
Phone: ++49-711-78055-19
E-Mail: mgalle@hpce.nec.com
Thorsten Schwarz
German Aerospace Center,
Braunschweig
Phone: ++49-531-295-2887
E-Mail: Thorsten.Schwarz@dlr.de
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