The datasets provided here are relatively small by today's standards, but provide examples of single and multi-zone overset meshes with associated scalar and vector fields, which may be useful for developing and testing geometric
and visualization routines.
Some of them, such as the blunt fin ("the teapot of CFD visualization"), have been used in innumerable studies, and continue to serve as historical references. These datasets are available to the scientific community for research,
study, and exploration, and can be duplicated and redistributed, as long as the principal investigators for the data are appropriately credited.
Blunt Fin
C.M. Hung and P.G. Buning,1984. Airflow over a flat plate with a blunt fin rising from the plate. Free stream flow direction is parallel to the plate and to the flat part of the fin, entirely in the x component direction.
The flow is assumed to be symmetrical about a plane through the center of the fin, so only one half of the "real" geometry is present and used in the computation. Steady, viscous flow, Mach 2.95, Re = 2.1e6.
Reference
C.M. Hung and P.G. Buning, "Simulation of Blunt-Fin Induced Shock Wave and Turbulent Boundary Layer Separation," AIAA Paper 84-0457, AIAA Aerospace Sciences Conference, Reno, NV, January 1984.
Data
The plate is found at K = 1, and the fin at j = 1.
The data are in plot3d, single-zone, binary. All floating point data are in 32-bit IEEE format, big endian.
Delta Wing at 40 Degrees Angle of Attack
J.A. Ekaterinaris and L.B. Schiff, 1990. Flow past a very simplified geometry representing a delta wing aircraft, at a moderately high angle of attack. Steady, viscous flow, Mach 0.3, alpha 40.0 degrees, Re 1e6.
Reference
J.A. Ekaterinaris and L.B. Schiff, "Vortical Flows over Delta Wings and Numerical Prediction of Vortex Breakdown," AIAA Paper 90-0102, AIAA Aerospace Sciences Conference, Reno, NV, January 1990.
Data
The modeled body surface covers the faces of the following grid cells:
top
i = ( 1 .. 40)
j = ( 2 .. 31)
k = ( 1 .. 1)
belly
i = ( 1 .. 40)
j = (31 .. 53)
k = ( 1 .. 1)
The data are in PLOT3D, single-zone, binary. All floating-point data are in 32-bit IEEE format, big endian.
Liquid Oxygen Post
S. E. Rogers, D. Kwak, U. Kaul, 1986. Liquid oxygen (incompressible) flow across a flat plate with a cylindrical post rising perpendicular to the plate (and therefore the flow). The simulation is modeling a flow internal to a
rocket engine. A Space Shuttle Launch Vehicle engine has a region in which many such posts obstruct the flow of liquid oxygen to promote better mixing. Steady, viscous flow, Re = 1000.
Reference
S. E. Rogers, D. Kwak, U. Kau, "A Numerical Study of Three-Dimensional Incompressible Flow Around Multiple Posts," AIAA Paper 86-0353, AIAA Aerospace Sciences Conference, Reno, Nevada, 1986.
Data
The data are in plot3d, single-zone, binary. All floating point data are in 32-bit IEEE format, big endian.
Wingbodytail
J.A. Benek, P.G. Buning, and J.L. Steger, 1985. Simple multizone geometry, steady flow.
References
J.A. Benek, P.G. Buning, and J.L. Steger, "A 3-D Chimera Grid Embedding Technique," AIAA-85-1523-CP, AIAA 7th Computational Fluid Dynamics Conference, Cincinnati, OH, July 15-17, 1985.
J.A. Benek, J.L. Steger, F.C. Dougherty, and P.G. Buning, "Chimera: A Grid-Embedding Technique," AEDC-TR-85-64, Arnold Engineering Development Center, Arnold AFS, TN, April 1986.
Data
PLOT3D, formatted, binary
Tapered Cylinder
D. Jespersen and C. Levit, 1991. Unsteady solution of viscous flow around a tapered cylinder. Re = 150, defined by cylinder radius at midspan. Vortex shedding at varying frequencies (related to varying cylinder radius) leads to
vortex tearing events.
Reference
Jespersen D, Levit C., "Numerical simulation of flow past tapered cylinder". AIAA Paper 91-0751, 29th Aerospace Sciences Meeting, Reno, NV, 7-10 January, 1991.
Data
The data are in plot3d, single-zone, binary format. All floating point data are in 32-bit IEEE format, big endian.
There is one grid file and approximately 400 solution files, one every 10 solution time steps. As the solution time step was 0.1 non-dimensional units, the time between solution files available here is 1.
The time between each solution file is 1.0 non-dimensional time units. The Reynolds number is 150 as defined by the cylinder radius at midspan. Flow is not periodic.
Space Shuttle Launch Vehicle
P.G. Buning, et. al., 1989. This simulation of the Space Shuttle Launch Vehicle has the shuttle in launch configuration, including the external tank, shuttle rocket boosters and some interconnection hardware. Only one half of the
geometry (and surrounding flow field) is represented, as the data is assumed to be symmetric about the central plane. The orbiter tail is missing from this geometric description. Steady, viscous flow, Mach 1.25, alpha -5.1 degrees,
Re 8e6.
References
P.G. Buning, I.T. Chiu, F.W. Martin, Jr., R.L. Meakin, S. Obayashi, Y.M. Rizk, J.L. Steger, and M. Yarrow, "Flowfield Simulation of the Space Shuttle Vehicle in Ascent," Fourth International Conference on Supercomputing, Vol II,
Supercomputer Applications, Kartashev & Kartashev, eds., 1989, pp. 20-28.
F.W. Martin, Jr. and J.P. Slotnick, ''Flow Computations for the Space Shuttle in Ascent Mode Using Thin-Layer Navier-Stokes Equations,'' Applied Computational Aerodynamics, Progress in Astronautics and Aeronautics, Vol. 125,
P.A. Henne, ed., American Institute of Aeronautics and Astronautics, Washington, D.C., 1990, pp. 863-886.
Data
The data are in PLOT3D, multiple-zone, iblank, binary. All floating point data are in 32-bit IEEE format, big endian.
There are nine grid blocks with dimensions:
Block 1: 88 x 39 x 60
Block 2: 92 x 57 x 28
Block 3: 98 x 77 x 48
Block 4: 24 x 33 x 23
Block 5: 33 x 33 x 22
Block 6: 25 x 40 x 21
Block 7: 75 x 37 x 33
Block 8: 14 x 25 x 30
Block 9: 53 x 23 x 50
