CFD codes list
This is the most recent version of the list. Converted version of
this document is regularly posted to
sci.physics.computational.fluid-dynamics
newsgroup.
I will be happy to hear about codes/links/sites not included in this
list. Please, e-mail me directly or post to the newsgroup. Each
contribution should contain short description of the method,
availability, author, etc.
Tomasz Plewa
Max-Planck-Institut für Astrophysik
Warsaw University Observatory
Mirror sites
U.S.
http://icemcfd.com/cfd/CFD_codes.html
Wayne Christopher
Italy
http://cdc715_0.cdc.polimi.it/~qua1390/Fluids/CFD_Codes.html
Massimiliano E. Rizzi
Wayne maintains also two other lists which are mirrored in Europe:
CFD books (U.S., Europe)
CFD Home pages (U.S., Europe)
Version
May 08, 1995
News
EnSight / CEI Inc.
Software for 3-D Fluid Interfaces (TVD/AC)
Legend
commercial (not freely available)
public-domain
shareware, freeware, other
-
UIFlow
Foil 1.0.2
SSIIM (3D water and sediment flow)
PORFLOW
PPM -- Piecewise Parabolic Method (DE and LR versions)
LCA codes for astrophysical simulation and visualization
General Relativity NCSA group (black hole evolution)
NACA airfoils
ARSoftware (TEP: a combustion analysis tool for windows)
NASA NAS (fluid mechanics and heat transfer)
College of Marine Studies (sci.geo.fluids models)
MOM (Modular Ocean Model)
Roe solvers (CLAWPACK library by Randall LeVeque)
Fluent Inc. (Fluent/V4, Fluent/UNS, Rampant, Nekton)
HEATING (a multdimensional heating conduction code)
PHI3D (3D FEM Navier-Stokes code)
HYDRO (2D Lagrangian hydrodynamics code)
Flowtech Int. AB (SHIPFLOW: analysis of flow around ships)
Fluid Dynamics International, Inc. (FIDAP)
CIT Thermoflow AB (CALC-BFC)
CFDS Inc. (CFDS-FLOW3D: 3D fluid flow/heat transfer code)
Smoothed Particle Hydrodynamics
Cullimore and Ring Technologies, Inc. (SINDA/FLUINT, SINAPS)
ICEM Systems Inc. (ICEM CFD, Icepak)
KIVA (reactive flows)
PHOENICS/CHAM (multi-phase flow, N-S, combustion)
CFD Research Corporation (ACE: reactive flows)
Computational Dynamics Ltd. (Star-CD: reactive flows)
Analytical Methods, Inc. (VSAERO, USAERO, OMNI3D)
STSWM (Spectral Transform Shallow Water Model)
FCT (Flux-Corrected Transport)
AeroSoft, Inc. (GASP)
Ithaca Combustion Enterprises (PDF2DS)
NASA LeRC (LPDF2D)
NSC2KE (N-S finite-volume Galerkin 2D code)
Flow Science, Inc. (FLOW3D)
Adaptive Research Corp. (CFD-2000)
ALGOR, Inc. (ALGOR)
Engineering Mechanics Research Corp. (NISA)
Reaction Engineering International (BANFF/GLACIER)
Combustion Dynamics Ltd. (SuperSTATE)
AVL List Gmbh. (FIRE)
IBM Corp. catalogue (30 positions)
Sun Microsystems catalogue (70 positions)
Cray Research catalogue (100 positions)
MDA Engineering, Inc. (GRIDGEN - structured grids)
Scientific Services, Inc. (N3S Finite Element code, MUSCL)
Directory of CFD codes on IBM supercomputer environment
Advanced Scientific Computing Ltd.
HENSA archive (FLUX, NSUVP, TEAM, VORTEX)
FEMLAB (2D FEM with automatic error control)
Collection of CFD codes for ship design
ANSYS, Inc. (FLOTRAN)
Silicon Graphics, Inc. catalogue (75 positions)
Riemann Problem Package
CHAMMP repository (s-w equations in spherical geometry)
NACHOS (NACHOS - FEM for incompressible flows)
FMS-1D (Fluid Modeling System)
Flomercis Inc. (FLOTHERM)
Computational Mechanics Corporation
NPARC Flow Solver
Computational Mechanics Company, Inc. (COMCO)
KASIMIR (shock tube simulation program)
Livermore Software Technology Corporation (LS-DYNA3D)
Advanced Combustion Eng. Research Center (PCGC, FBED)
NUMECA International s.a. (IGG, EURANUSturbo, ...)
Computational Engineering International., Inc. (EnSight, ...)
Software for 3-D Fluid Interfaces (TVD/AC)
link to UIFLOW
Article: 177 of sci.physics.computational.fluid-dynamics
>From Richard Hilson /
hilson@pde1.mtv.gtegsc.com
Subject: UIFlow and Post3D
Date: 29 Apr 94 12:23:14 -0800
I got a copy of the 2D CFD code *UIFlow* from NCSA for the Mac. It seems
to work For those who are interested, UIFlow can be found in
ftp.ncsa.uiuc.edu (141.142.20.50) in the file /mac/uiflow.
link to Foil
Article: 193 of sci.physics.computational.fluid-dynamics
>From Robin B. Lake /
rbl@hal.cwru.edu
Subject: Airfoil Program for Mac Available
Date: 3 May 1994 00:34:46 GMT
I happened across a program in the info-mac archives at sumex-aim.stanford.edu
today. To my surprise, it turns out to be:
"This is the ReadMe file for Foil 1.0.2, a Macintosh airfoil generation and
display program. Foil 1.0.2 is System 6/7 happy, meaning it should run equally
well under both systems. Foil is free, but not public domain. I retain all
rights, and it may not be distributed in modified form, or without any of the
files. Since it's free, please read the file "A Note About the Author".
links to SSIIM:
ugle.unit.no, ftp.cdrom.com.
>From Nils R. Olsen /
Nils.R.Olsen@nhl.sintef.no
Date: Tue, 26 Jul 1994 21:38:53 GMT-0100
MODEL PURPOSE AND STRUCTURE
SSIIM is an abbreviation for Sediment Simulation In Intakes with
Multiblock option. The program is made for use in
River/Environmental/Hydraulic/Sedimentation Engineering. The main
motivation for the program is to simulate the sediment movements in
general river/channel geometries. This has shown to be difficult to do
in physical model studies for fine sediments.
The program solves the Navier-Stokes equations with the k-epsilon model
on a three-dimensional almost general non-orthogonal grid. The grid is
structured. A control volume method is used for the discretization,
together with the power-law scheme or the second order upwind scheme.
The SIMPLE method is used for the pressure coupling. The solution is
implicit, also over the boundary of the different blocks. This gives the
velocity field in the geometry. The velocities are used when solving the
convection-diffusion equations for different sediment sizes. This gives
trap efficiency and sediment deposition pattern.
The model has a user interface with capabilities of presenting graphical
plots of velocity vectors and scaler variables. The plots show a
two-dimensional view of the three- dimensional grid. Three plots showing
the geometry from above, in a cross-section and in a longitudinal
profile are available. In addition it is possible to simulate particle
animation for visualization purposes.
The model includes several utilities which makes it easier to give input
data. The most commonly used data can be given in dialog boxes. Several
of the modules in the program can be run simultaneously as separate
threads. This exploits the multi-tasking capabilities in OS/2. There is
an interactive graphical grid editor with elliptic and transfinite
interpolation. Grid and some of the input data can be changed during the
calculation. This can be useful for convergence purposes, and also when
optimizing the geometry with respect to the flow field.
AVAILABILITY
The program is freeware and can be downloaded from the following addresses:
- "ugle.unit.no" from the directory "/pub/os2/ssiim".
- "ftp.cdrom.com" from the directory "/pub/os2/2_x/educate"
OPERATING SYSTEM:
The program runs only under OS/2 2.x.
CONTENT OF SSIIM13.ZIP
- "readme.ssi" : readme file
- "changes.23" : a summary of the most important changes from version
1.2 to version 1.3
- "manual.wp" : User's Manual, written in WP5.1
- "ssiim13.exe" : executable file, optimized for the 486 processer
- "ssiim13p.exe" : executable file, optimized for the Pentium processer
In addition there are input files for four examples. The examples are further
described in Chapter 5.3 in the User's Manual
Nils Reidar Olsen
E-mail: Nils.R.Olsen@nhl.sintef.no
Article: 380 of sci.physics.computational.fluid-dynamics
>From Zlatko Rek /
Zlatko.Rek@ijs.si
Date: 31 May 94 07:51:15 GMT
PORFLOW - a model for fluid flow, heat and mass transport in multifluid,
======= multiphase, fractured or porous media
Analytic & Computational Reasearch Inc.
3106 Inglewood Boulevard
West Los Angeles
CA 90066
(213) 398-0956
Colella, P., Woodward, P.R., 1984, J. Comput. Phys., 54, 174.
PPM is high-order (3/2), shock-capturing
Godunov-type method.
Before using PPM take a look at
some papers,
and read infomation about
DE
and
LR versions.
Direct Eulerian version
Tomasz Plewa
Warsaw University Observatory
plewa@sirius.astrouw.edu.pl
Date: 10 Jun 94
link to DE version
DE version is generally accessible through WWW ftp link.
Please, let me know if you have no access to WWW server.
Lagrangian Remap version (1)
Greg Lindahl
University of Virginia
gl8f@fermi.clas.virginia.edu
Date: 29 Jun 94
link to LR version
Lagrangian Remap version (2)
Virginia Hydrodynamics-1
Theoretical Astrophysics,
Dept. of Physics
NCSU
Date: 03 Apr 95
Thanks to Robert Fiedler / LCA
Laboratory for Computational Astrophysics
National Center for Supercomputing Applications
University of Illinois at Urbana-Champaign
5257 Beckman Institute
405 N. Mathews Ave.
Urbana, IL 61801
INTRODUCING THE LABORATORY FOR COMPUTATIONAL ASTROPHYSICS
The LCA is a joint venture between the NSF, the National Center for
Supercomputing Applications, and the Department of Astronomy at the
University of Illinois, Urbana-Champaign. Its purpose is to develop
and disseminate numerical algorithms and community codes for CFD,
primarily for astrophysics.
The LCA currently provides the following packages:
* ZEUS-2D: a one- or two-dimensional (moving) Eulerian grid code
for radiation magnetohydrodynamics.
* ZEUS-3D: a one-, two- or three-dimensional explicit (moving)
Eulerian grid code for magnetohydrodynamics.
* TITAN: a one-dimensional implicit adaptive mesh code for
radiation hydrodynamics.
* 4D2: an interactive tool for visualizing and animating 3D
data (array, particle) on Silicon Graphics workstations.
The community application codes (ZEUS-2D, ZEUS-3D, TITAN) are available
free of charge to academic researchers.
LCA Home Page and
software.
Relativity Group
National Center for Supercomputing Applications
University of Illinois at Urbana-Champaign
Home Page
and
summary.
ONEDBH (no source here?)
ONEBH (overview
and source)
3D codes front end.
Collection of articles and links related to NACA airfoils is
here.
ARSoftware
The Science and Technical Software Company
Electronic Publishers and Distributors
8201 Corporate Drive, Suite 1110
Landover, Maryland 20785
FAX (301) 459-3776
e-mail
west@arsoftware.arclch.com
What is TEP?
List
of commercial software.
README file and
ftp link.
ftp
Geophysical Fluid Dynamics Laboratory
GFDL Home Page and
MOM page.
Randall J. LeVeque
Applied Mathematics Dept., FS-20
University of Washington
Seattle, WA 98195
rjl@amath.washington.edu
CLAWPACK -- Conservation LAWs software PACKage
------------------------------------------------
Version 1.0 of CLAWPACK is now available from netlib. This is a package of
Fortran subroutines for solving hyperbolic systems of conservation laws in one
and two space dimensions. (Future versions should include 3D.) High resolution
flux-limiter methods are used, based on solving one-dimensional Riemann
problems. In two dimensions, multi-dimensional wave-propagation methods are
used. The current version supports only uniform Cartesian grids in
rectangular domains, and is intended primarily as a research and teaching
tool. The modular form should make it easy to modify and experiment with
other methods, as well as to apply it to new problems.
The code requires that the user supply a Riemann solver for the problem
being solved and also a subroutine that implements the boundary conditions.
Source terms can also be handled (via Strang splitting) in which case an ODE
solver for the source terms must also be supplied. Several examples of
different Riemann solvers are included with the package, including e.g.,
advection equation, Burgers' equation, Euler equations, isothermal
equations, shallow water equations. Various different boundary conditions
are also demonstrated, such as periodic, inflow, nonreflecting, and solid
walls. Numerous example drivers are included to demonstrate the use of
these subroutines. Matlab m-files are included to graphically display the
output, or they can be used as a model for writing graphics routines in
other languages. Documentation is included in the package, including the
postscript file for an introductory paper on the package.
The package can be obtained from netlib, where it resides in the library
pdes/claw. This directory currently contains:
index the index
clawpack the basic package, with 1d, 2d routines and many examples
doc documentation (postscript files of papers, slides)
advection applications of clawpack to 2d advection equations, with
examples from a recent paper on this subject (in doc).
nozzle application of clawpack to the quasi-1d nozzle problem.
vBurgers viscous Burgers' equation, with diffusion equation as source.
L-domain L-shaped domains, such as the forward facing step problem.
My hope is that a library of more sophisticated applications
will be gradually built up, and contributions from other users will be
gratefully accepted.
The package may be obtained by anonymous ftp from
netlib.att.com,
where it resides in
netlib/pdes/claw.
The file
netlib/pdes/claw/clawpack.shar
is a tar file of
the entire directory. Files can also be obtained by sending e-mail to
netlib@research.att.com.
Send the message "help" to this address for more
information. Alternatively, you can obtain files by ftp through Mosaic using
the URL
ftp://netlib.att.com/netlib/pdes/claw/index.html
.
It is also possible to browse through the library using Mosaic from
ftp://amath.washington.edu/pub/leveque/programs/clawpack.html
.
Fluent Inc. /
info@Fluent.COM
Centerra Resource Park
10 Cavendish Court
Lebanon, NH 03766-1442
tel: 603.643.2600, 800.445.4454
fax: 603.643.3967
Fluent Inc. distributors around the world
and CFD software
packages. For more information contact
info@Fluent.COM.
Kenneth. W. Childs /
kch@ornl.gov
Heat Transfer and Fluid Flow Group
Oak Ridge National Laboratory
HEATING is a general-purpose, conduction, heat transfer program
written and maintained by the Heat Transfer and Fluid Flow Group
(HTFFG).[...]
More about HEATING.
>From Jonas T. Holdeman, Jr. /
hol@ornl.gov
Date: Tue, 07 Feb 1995 15:09:52 -0500
I understand both workstation and PC versions of the HEATING code are
available freely from the authors, Gary Giles (geg@ornl.gov) and Ken Childs
(kch@ornl.gov). [...] Please check with the authors for latest
information.
Paul T. Williams /
ptw@ornl.gov
Heat Transfer and Fluid Flow Group
Oak Ridge National Laboratory
As a part of validation studies for the locally developed finte-element
incompressible Navier-Stokes Code PHI3D [...]
More about PHI3D.
>From Jonas T. Holdeman, Jr. /
hol@ornl.gov
Date: Tue, 07 Feb 1995 15:09:52 -0500
PHI3D was developed by Paul Williams (ptw@ornl.gov) for his Ph.D.
dissertation. He says it needs to be cleaned up before he will release it.
If someone were willing to give him some funding, this process could be
speeded up, as he has no funding to work on the code at present.
>From Hao Chen /
hchen@s1.msi.umn.edu
ftp link
Los Alamos National Laboratory
Benchmarking Section of Group C-3
Dennis V. Brockway, Fred Gama-Lobo, Karl Wallick, John Romero, & Steve W. White
May 1, 1984
HYDRO.DOC
ABSTRACT: This is a two-dimensional Lagrangian hydrodynamics code based on
an algorithm of W.D. Schultz.
NUMERICAL: According to the report below, HYDRO is representative of a large
class of codes used in the Los Alamos Laboratory and is 100%
vectorizable.
NOTES: HYDRO is very similar to SIMPLE - Almost identical methods.
However, HYDRO can handle General Geometry, while SIMPLE uses Fixed
Geometry (Equation of state table 2X2)
AUTHORS: produced under U.S. government contract (w-7405-eng-36)
by Los Alamos National Laboratory
by D. Brockway, F. Gama-Lobo, K. Wallick, J. Romero, S. White
Contact benchmarking section of group c-3 LANL (505)667-7028
REFERENCES: Report: Los Alamos Laboratory Computer Benchmarking 1988
H.J. Wasserman
William D. Schulz
Methods of Computational Physics
Volume 3, 1964
>From Johannes Schoon /
schoon@na.chalmers.se
Date: Tue, 21 Jun 94 09:57:21 +0200
Flowtech International AB
Box 24001
S-400 22 Gothenburg
Sweden
tel.&fax. int.+46 31 41 50 60
[...] SHIPFLOW. As the name suggests, this code is good for
design/analysis of flow around ships. It uses a non-linear free surface
panel method, a boundary layer method and a Reynolds averaged
Navier-Stokes method to calculate wave-making resistance, skin friction
resistance, sinkage etc for the modern Naval Architect.
FIDAP
Fluid Dynamics International, Inc.
500 Davis Street, Suite 600
Evanston, IL 60201 USA
phone (708) 491-0200
fax (708) 869-6495
Date: Mon, 4 Jul 94 11:49:22 PDT
FIDAP Fluid Dynamics Analysis Package uses a finite element
approach for analysis of fluid & heat flow problems. Options are
included for incompressible and compressible flow, laminar and
turbulent flow, single and 2-phase flow, Newtonian or non-Newtonian
rheology, heat flow by conduction, convection, and radiation, heat
sources and sinks, solidification and melting, and lots more.
The software includes mesh generation, data input, solution, and
post-processing data visualization.
Software versions of FIDAP (as of 1/93) are available for these
computers: CONVEX, CRAY, DEC, FUJITSU, HEWLETT-PACKARD, IBM,
SILICON GRAPHICS, STARDENT, and SUN. There's also a PC-version.
For an example of the use of FIDAP, see: Thomas, B.G. and F.M. Najjar,
1991, Finite element modelling of turbulent fluid flow and heat
transfer in continuous casting, Applied Math. Modelling, 15: 226-243.
Lars Davidsson /
lada@tfd.chalmers.se
CIT Thermoflow AB
Chalmers Teknikpark
S-421 88 Gothenburg
Sweden
tel. int.+46 31 772 14 04 (or .... 10 00)
fax. int.+46 31 18 09 76
CALC-BFC is a program which has been developed at the dept. of Thermo and
Fluid Dynamics here at Chalmers. It has now grown into a commercial code.
>From David Bailey /
david.bailey@aea.orgn.uk
CFDS-FLOW3D
-----------
A general purpose 3D fluid flow and heat transfer code, including combustion
and multi-phase flow.
CFDS CFDS Inc.
AEA Technology 1700 N. Highland Road
8.19 Harwell Suite 400
Didcot Pittsburgh
Oxon USA
UK
Tel: +44 (0)235 432101 Tel: 412 833 4820
+44 (0)234 432989
Fax: +44 (0)234 436671 Fax: 412 833 4580
email: cfds.sales@aea.orgn.uk
>From Brent Cullimore /
crtech@netcom.com
Cullimore and Ring Technologies, Inc.
49 Dawn Heath Circle
Littleton Colorado 80127-4303
(303) 971-0292
crtech@netcom.com
Note that there is a new ftp site:
ftp://ftp.csn.net/crtech
and a new home page:
http://www.webcom.com/~crtech.
C&R Technologies is pleased to announce the availability of a new anonymous
ftp site containing FREE SOFTWARE and other information related to our
heat transfer and fluid flow simulation code SINDA/FLUINT and its graphical
user interface, SINAPS.
============================== SINDA/FLUINT ===================================
A comprehensive finite-difference lumped-parameter tool for analyzing complex
thermal/fluid systems. Suitable for both preliminary design and point design
simulation, at both the component and system level. SINDA/FLUINT is used at
over 300 sites in the aerospace, energy, electronic, HVAC, medical, and
automotive industries.
Capabilities include: steady and transient analyses, radiation, convection, and
conduction heat transfer, single- and two-phase flow, fluid mixtures, time- and
temperature-varying properties, and user logic for control and customization.
Applications include thermal and environmental control, propulsion, electronics
packaging, and power generation.
================================= SINAPS ======================================
A modern graphical user interface to SINDA/FLUINT. Enables users to sketch
thermal/fluid circuits, validate/preprocess inputs interactively, and then
visualize, interpret, and report results graphically.
Capabilities include: algebraic and functional in-puts; depiction of large,
complex networks, colorization by value, animation through time, and pop-up
X-Y, bar, and polar plots.
============================== Availability ===================================
Sun Microsystems SPARCstations(tm), SunOS 4.1.X or Solaris 2.X
Hewlett-Packard Apollo(tm) Series 700 Workstations
IBM PCs and 100% compatibles
Apple Macintosh(tm) II
=========================== About the ftp site ================================
A README file contains a current description of the site contents. The site
contains:
(1) Newsletters, announcements, and patches (as available)
(2) Product information, brochures, and SINAPS pictures
(3) New tutorial introductions to SINDA, FLUINT, and SINAPS
(4) SINDA/FLUINT Version 3.0. Fully functional copies of SINDA/FLUINT
limited to 50 thermal nodes and 10 fluid lumps. This is enough to
run most of the (provided) SINDA/FLUINT sample problems, as well
as student or evaluation problems.
(5) SINAPS Version 2.1 demo. Enables full evaluation of SINAPS without
the ability to save work in progress. Together with a copy of
SINDA/FLUINT, you can develop, preprocess, launch, and postprocess
your own model, or you can experiment with sample problems.
PLEASE TAKE NOTE OF THE LICENSE AGREEMENT AND SYSTEM REQUIREMENTS BEFORE DOWN-
LOADING OR INSTALLING THESE CODES. SINDA/FLUINT requires a specific Fortran 77
compiler on each machine (which regrettably are not ours to offer for free).
SINAPS requires 16MB RAM on personal computers (PC/Mac), 32MB on workstations
(Sun/HP).
All of the code and documentation we would ideally like to provide may not yet
be available on this site. If you do not find what you need, or would like a
different format, media, etc., please contact us and we can either update the
site and/or send disks, hardcopies, etc.
--
_______
_____ \| \\
// \| || || Cullimore and Ring Technologies, Inc.
|| | ||___// 49 Dawn Heath Circle
|| || \\ Littleton Colorado 80127-4303
|| || \\ (303) 971-0292
\\ || \\ crtech@netcom.com
==========================================================================
Thermal/Fluid System Design and Analysis
>From Wayne A. Christopher /
faustus@remarque.berkeley.edu
ICEM Systems, GmbH
US distributor: ICEM CFD Engineering of Berkeley, CA
For more information contact
info@icemcfd.com
ICEM CFD
ICEM CFD
is a computational grid generation system developed by ICEM
Systems, GmbH, and
ICEM CFD Engineering of Berkeley, CA. It is sold and supported in
the United states and Canada by ICEM CFD Engineering.
ICEM CFD is known for its ability to generate high-quality
grids based on arbitrary CAD surface data, created either in the ICEM
system or imported from other CAD systems using standard interfaces such
as IGES. It includes both multi-block structured and unstructured mesh
generation tools, and can create input for a wide variety of flow solvers.
Icepak
Icepak
is an object-oriented thermal analysis system for electronic
components. It was developed by
ICEM CFD Engineering of Berkeley, CA, and Fluid Dynamics
International of Evanston, Il.
Icepak includes an object-based modeling system, which allows users
to rapidly create complex models with pre-defined component types,
a fully automatic hexahedral grid generator that creates body-fitted
high-quality grids, the Fidap flow solver, and extensive post-processing
capabilities.
For more information, please take a look at our
WWW page, or contact
Mary Jo Hamilton (mj@icemcfd.com, (508) 497-2341).
for more information search
OSTI WAIS gate
with keyword KIVA
Article: 576 of sci.physics.computational.fluid-dynamics
>From Robin B. Lake /
rbl@hal.cwru.edu
Date: 10 Jul 1994 14:52:30 GMT
In article <2vo5bn$5jl@news.u.washington.edu> hinkey@aa.washington.edu (John Hinkey) writes:
>
>Does anyone know of any CFD codes capable of
>modeling a two-phase detonation, i.e. a
>gaseous oxidizer with a solid or liquid fuel
>suspended in it?
>
There is a code "KIVA" that BP uses for such explosive environments as
internal combustion engine cylinders. In that it can handle chemical
transformations, it may be suitable.
In that BP has reorganized and eliminated its US Research, I can't give
you the name of any competent staff at their Sunbury-on-Thames Research
Centre in the UK. You might try to contact Dr. Wendell Mills, Engineering
Computing Inc., who occupies space at BP's former Warrensville Research
Center in Cleveland. Call the central BP number in Cleveland. Can't help
much, as they've changed the phone numbers recently (and probably the
locks, too!).
Rob Lake
Environmental Modeling Inc.
rbl@hal.cwru.edu
>From Necdet Kurul /
kuruln@rpi.edu
Date: Tue, 12 Jul 1994 22:15:51 -0400
Another code is PHOENICS of CHAM.
It does:
- Single as well as multi-phase flow simulations,
- laminar and a variety of turbulent flow simulations,
- solving additional equations on top of Navier-Stokes eqs.,
such as those in combustion, chemical processes etc.
More information can be found from mscv21@sf.msc.edu.
>From Andre van Niekerk /
niekerk@civen.civil.wits.ac.za
Date: Fri, 17 Feb 1995 14:20:12 GMT
CHAM have also put out a shareware version of PHEONICS (it's versions 1.4).
Andre van Niekerk
Dept of Civil Engineering
Wits University
Johannesburg
Link to
PHOENICS V 1.4 Sharware.
Article: 646 of sci.physics.computational.fluid-dynamics
>From Lyle Johnson /
ljohnson@acenet.auburn.edu
Date: Mon, 25 Jul 1994 14:25:03 GMT
Subject: Re: Need addresses of Fidap/Fluent and others
In ingle@acsu.buffalo.edu (Nitin K. Ingle)
writes:
>Hello,
> Is it possible to get the names and addresses of vendors who
>have developed CFD (Computational Fluid Dynamics) and reacting flow
>codes? For example the developers of packages like Fluent, Fidap,
>Flow3D etc. I would appreciate if anyone can provide me with this
>list or direct me where to obtain one.
>Thanks in advance,
>Nitin Ingle
May I suggest CFD-ACE, produced by CFD Research Corporation?
CFD Research Corporation
3325 Triana Blvd.
Huntsville, Alabama 35805
Phone: (205) 536-6576
Contact: R. Sukumar
Article: 656 of sci.physics.computational.fluid-dynamics
>From H.W. Krus /
hwkrus@inter.NL.net
Subject: Re: Need addresses of Fidap/Fluent and others
Date: Tue, 26 Jul 1994 06:37:36 GMT
Lyle Johnson (ljohnson@acenet.auburn.edu) wrote:
: In ingle@acsu.buffalo.edu (Nitin K. Ingle) writes:
: >Hello,
: > Is it possible to get the names and addresses of vendors who
: >have developed CFD (Computational Fluid Dynamics) and reacting flow
: >codes? For example the developers of packages like Fluent, Fidap,
: >Flow3D etc. I would appreciate if anyone can provide me with this
: >list or direct me where to obtain one.
: >Thanks in advance,
: >Nitin Ingle
Hi,
Here's another one:
The makers of Star-CD (also reacting, e.g. engine combustion):
Computational Dynamics Ltd.
Olympic House
317 Latimer Road
London W10 6RA
Tel. +44-81-969 9639
Fax. +44-81-968 8606
Email riaz@cd.co.uk (the adress of one of CD's people)
Henk
>From Devadatta Mukutmoni /
mukut@panix.com
Date: 22 Sep 1994 23:17:02 -0400
STAR-CD: It is a commercial general-purpose code based on the
finite-volume method. The formulation is for a completely unstructured
grid.
It is made by Computational Dynamics based in London, UK.
The North-American distributor is Adapco based in Melville, NY.
Devadatta Mukutmoni
e-mail: mukut@panix.com, mukut@adapco.com
>From Burke Murray /
hedmips!burke@uunet.uu.net
Date: Tue, 2 Aug 1994 09:53:14 -0400 (EDT)
We write and sell several CFD codes, but the two most popular are:
VSAERO: 3D steady flow panel method
USAERO: 3D unsteady flow panel method
We also sell a postprocessor called OMNI3D which works with both VSAERO
and USAERO.
Burke Murray
Analytical Methods, Inc.
P.O. Box 3786
Bellevue, WA 98009
USA
Phone: (206) 643-9090
Fax: (206) 746-1299
internet: burke@hedmips.com
Here is more detailed information provided by David Lednicer of AM, Inc.
-VSAERO: A full configuration, subsonic aeroynamics analysis method that
solves the linearized potential flow equations. VSAERO uses
piecewise constant singularity strengths on surface panels to
represent arbitrary three-dimensional configurations. Boundary
layer calculations can be performed along on-body streamlines and
the resulting boundary layer thicknesses can be used to iteratively
correct the inviscid flowfield (using surface transpiration).
Compressibility corrections are available within the program
for higher subsonic Mach number cases. Wake geometry is determined
by an iterative wake shape calculation procedure. Special purpose
modules such as; WHIP, ROTOR and PROPFAN expand VSAERO's capabilities.
These modules calculate the nonlinear hydodynamic wave effects on
surface piercing vessels, helicopter rotor/fuselage interactions and
propeller/fan performance, respectively.
-USAERO: This program calculates the transient aerodynamic
characteristics of complex configurations in arbitrary motion.
It is based on a time-stepping procedure which allows relative
motions of configuration components. USAERO simulations include
manuevering aircraft, gust response, rotor/body interactions and
stores separation from aircraft. Special application modules FPI
and FSP couple with USAERO to provide flight-path integration
calculations with six degrees of freedom and ship motion calculations
with nonlinear free-surface simulation.
-MGAERO: A 3-D Euler method for computing flow about arbitrary
configurations in the subsonic through supersonic flight regimes.
It uses a multigrid approach with an equally-spaced Cartesian
mesh structure including local refinement. Swept, unswept and
rotated grids may be used to develop local computational domains
which may be overlapped with either the surface or other multigrid
levels. The ease of geometry and grid input allows for rapid
turnaround of results for complete aircraft, including nacelles.
-OMNIPLOT: This is a post-processing program which displays the results
of 3-D aerodynamic calculations. Options include viewing surface
pressure, velocity and Mach number contours, on- and off-body
streamline trajectories, boundary layer calculation results and
off-body velocity survey data.
-OMNI3D: A color graphics visualization program which displays simulation
results in 3-D and arbitrary 2-D slices. It shows surface pressure,
velocity and Mach number contours on the body and in the flow field,
streamline and boundary-layer parameters along on- and off-body
streamline trajectories and wake geometry data. Time steps and
iterations may be animated or stepped through. OMNI3D's mouse-driven
interface and fast graphics permit rapid assessment of results on
complex configurations.
-ICE: This code calculates particle trajectories in the vicintity of an
arbitrary aircraft for use in icing and sand-ingestion analyses. The
efficient trajectory calculation and prescribed velocity field result
in a very fast calculation. ICE reads the aircraft geometry and
flowfield velocity from an OMNIPLOT/OMNI3D graphics file.
-XFOIL: An interactive program for the design and analysis of subsonic
airfoils. It consists of a collection of menu-driven routines which
perform functions such as; viscous (or inviscid) analysis of an
existing airfoil, airfoil design and redesign by interactive
specification of a surface speed distribution, airfoil redesign by
interactive specification of new geometric parameters. XFOIL is
based upon a linear-vorticity stream function panel method, coupled
to a two-equation, lagged dissapation integral boundary layer
formulation.
-MSES: A coupled viscous/inviscid Euler method for the analysis and
design of multi-element (and single-element) airfoils. A
streamline-based Euler discretization and a two-equation integral
boundary layer formulation are coupled through the displacement
thickness and solved simultaneously by a full Newton method. MSES
is capable of multi-point optimization of single- and multi-element
airfoils. The full Newton solution method of the solver permits
effectively "free" calculation of the flowfield sensitivities to
predefined element shape deformation modes and element translation
and rotation modes.
-MISES: A coupled viscous/inviscid Euler method for the analysis an
design of cascades. The internal formulation of this code is
much like that of MSES's.
-CAMRAD II: An aeromechanical analysis of helicopters and rotorcraft that
incorporates a combination of advanced technology, including
multibody dynamics, nonlinear finite elements, structural dynamics
and rotorcraft aerodynamics. For the design, testing and evaluation
of rotors and rotorcraft, CAMRAD II calculates performance, loads,
vibration, response and stability.
All computers codes are commercial products marketed by Analytical
Methods, Inc. Address inquries to:
-------------------------------------------------------------------
David Lednicer | "Applied Computational Fluid Dynamics"
Analytical Methods, Inc. | email: dave@amiwest.com
2133 152nd Ave NE | tel: (206) 643-9090
Redmond, WA 98052 USA | fax: (206) 746-1299
>From Hao Chen /
hchen@s1.msi.umn.edu
ftp link
File: README
SPECTRAL TRANSFORM SHALLOW WATER MODEL (Version 2.0)
Copyright (C) 1992
University Corporation for Atmospheric Research
All Rights Reserved
Ruediger Jakob
National Center for Atmospheric Research
Boulder, CO 80307-3000
August 1992
Contents
--------
1. Software Distribution Conditions
2. Description of Software
3. Directory of Files
4. Corrections and Changes
[...]
Another version of this code (or postprocessor?) is called
REFSOL. REFSOL
uses netcdf package. I'm not familiar with all this stuff...
link to URL document
Overview
Flux-Corrected Transport (FCT) is a conservative, monotone technique for
integrating generalized continuity and hydromagnetic equations. [...]
FCT was the first of the class of high-order, monotone schemes for solving
generalized continuity equations (e.g., the equations of Eulerian hydrodynamics). An
FCT bibliography of basic papers is posted here.
A suite of FCT modules with test programs is being developed for posting to the
HPCC/ESS Software Exchange. [...]
The software for solving 2D hydrodynamical problems will be found in the package
LCPFCT2. For 2D magnetohydrodynamical (MHD) applications, the package
MHDFCT2 also will be needed. Similar software packages LCPFCT3 and
MHDFCT3 eventually will be posted for solving 3D problems.
[...]
C. Richard DeVore
Laboratory for Computational Physics & Fluid Dynamics, Naval Research
Laboratory
>From Andrew Godfrey /
godfrey@amadeus.aerosoft.vt.edu
Date: Fri, 02 Sep 1994 10:07:18 -0400
The General Aerodynamic Simulation Program (GASP) efficiently models
the time-dependent, three-dimensional, Reynolds-Averaged, Navier-Stokes
equations and all subsets (1-D, 2-D, Axi-symmetric, TLNS, PNS, Euler).
GASP's abridged list of features are:
o Finite-volume, characterisitic-based, upwind methods.
o 28 multi-specie, chemistry models.
o 6 thermodynamic models.
o 5 tranport property models.
o Frozen, equilibrium, or finite-rate chemistry.
o Multi-zone, mesh sequencing.
o AF, GMRES, charateristic time stepping, inner iteration options.
o Algebraic and two-equation turbulence models.
o Graphical user interfaces.
Developed, supported and marketed commercially by:
AeroSoft, Inc.
1872 Pratt Drive, Suite 1275
Blacksburg, Va. 24060-6363
(703) 231-6125
>From Andrew Norris /
fsandy@icomp01.lerc.nasa.gov
Date: Wed, 7 Sep 1994 10:03:59 -0400
pdf2ds - 2D velocity, dissipation, composition pdf method for
combustion calculations. Author Steve Pope.
Available from Ithaca Combustion Enterprises.
Commercial.
Written in fortran 77; available on work-stations.
>From Andrew Norris /
fsandy@icomp01.lerc.nasa.gov
Date: Wed, 7 Sep 1994 10:03:59 -0400
lpdf2d - 2D Scalar pdf method for compressible combustion calculation.
Author A. Norris and A. Hsu.
Available from NASA Lewis Research Center.
Freeware, but only to companies/people in the United States.
Written in fortran 77; available on work-stations.
Bijan Mohammadi
INRIA-MENUSIN
Domaine de Voluceau
BP 105
78153 Le Chesnay, Rocquencourt
FRANCE
mohamadi@menusin.inria.fr
2D and AXI Euler and Navier-Stokes equations solver
o explicit multi-steps time integration process
o upwind schemes and linear interpolation method for
the computation of the convective fluxes using a finite
volume formulation.
o classical central galerkin p1-finite element method
for the computation of the diffusive fluxes
o k-epsilon turbulence model with two-layer approach or wall laws
Copyright(C) 1994 Bijan Mohammadi-Stephane Lanteri
Abstract
and
user guide.
>From James D. Freels /
fea@fea.rrd.ornl.gov
Date: Tue, 27 Sep 94 10:48 EDT
_______________________________________________________________________________
Code Company comments
FLOW3D Flow Science, Inc. finite-difference (FAVOR)
1325 Trinity Dr. explicit time step
P.O. Box 933 moving boundaries
Los Alamos, NM 87544 free surfaces
CFD-2000 Adaptive Research Corp. ?
4960 Corporate Dr., Suite 100-A
Huntsville, AL 35805
ALGOR ALGOR, Inc. finite-element
150 Beta Dr. large number of structural
Pittsburgh, PA. 15238-2932 users
no e-mail
NISA Engineering Mechanics Research Corp. finite-element
P.O. Box 696 large number of structural
Troy, Michigan 48099 users
>From Sandeep Jaivant Khatkhate /
sandeep@opus.utah.edu
Date: Tue, 27 Sep 94 13:20:52 -0600
BANFF/GLACIER - specialize in simulating three dimensional combustion
applications - marketed through REI based in SLC, UTAH. GLACIER is an
extension of BANFF that includes turbulent particle dispersion and
reaction. the cfd is done using a finite-volume approach and particles are
coupled using a Lagrangian cloud formulation.
-it can handle complex three-dimensional geometries
-full coupling between turbulent fluid and particle mechanics , radiative
and convective heat transfer and chemical reactions in multiple phases.
- typical applications are burner and furnace design, utility boilers,
waste incineration, pulverized coal combustion, other cfd applcations
including those involving turbulent particle transport.
REI stands for Reaction Engineering International (I think) and they are
based in Salt Lake City. The person whose email I have is Prof. Phil
Smith who works for REI. His email : smith@opus.utah.edu
Article: 956 of sci.physics.computational.fluid-dynamics
>From Albert Sulmistras /
albert@combdyn.com
Subject: Re: Opinions wanted: Finite Element FCT
Date: Wed, 28 Sep 1994 20:33:47 GMT
In article <367to4$ohu@fileserv.aber.ac.uk>, ssw@aber.ac.uk (Mr.Door) writes:
> Greetings,
> Part of my PhD work involves the use of two-dimensional FCT codes to
> simulate detonation phenomena. This work is now moving towards the
> simulation of shocks/detonations passing over irregular obstacles
> (say, shocks against wedges) which is something that my existing code
> isn't too good at.
SNIP...
> o Are there any other schemes around which allow relatively
> painless simulation of shocks over irregular obstacles - speed
> isn't that much of an object, but accuracy is. Eulerian
> schemes are preferred, since that's what I'm used to.
If the objective is to model shocks and detonations in complex 2-D
and 3-D geometries, the FE approach is NOT the only way to go.
We (Combustion Dynamics) developed an Euler code using FCT 6th
order in a rectilinear grid. Complex solid shapes can be defined
in the calculation domain. We then detect all solid surfaces and
use Reimann solvers across the boundary and impose free-slip
conditions at the surface. The benefit being that the whole
problem setup only requires several minutes... really :^) and
you do not need complex grid generators. For a detonation model,
we currently have one-step and two-step combustion models.
For equilibrium or chemical kinetic modelling of shocks and
detonations (i.e. ZND profile, CJ parameters, reflected shocks, etc.)
you can let your big cheese (Geraint) know that a beta version of
"SuperSTATE" will be heading his way shortly (depending on your
definition of short :^) ).
Regards, Albert
CFD-Department
Kleiststrasse 48
A-8020 Graz
Austria
Tel.: +43 316 987-441
FAX : +43 316 987-777
FIRE is an in house development of AVL List Gmbh. FIRE is based on a finite
volume differencing scheme using a modified variant of the SIMPLE
algorithm for the solution of
- compressible and incompressible flows
- steady state or time dependent flows
- higher order differencing schemes
- local (embedded) mesh refinement
- k-epsilon, RNG or refined (nonlinear) RSM turbulence model
- Injection Spray model
- Wallfilm model
- Combustion models (eddy breakup, PDF, diesel autoignition ...)
- Conjugate Heat Transfer problems
- moving geometries
- structured and unstructured grids of arbitrary complexity
- and much more ...
FIRE comes with an easy to use, fully interactive Pre - and Postprocessor.
The applications range from transient automotive to medical engineering flows.
Our
FIRE Web Server has an extensive collection (86 html documents, 44 gif's and 9 mpegs) of information regarding
FIRE. You are welcome to surf through our cyber space.
Fluids, CFD, Flow Analysis
>From Joy Crisp /
joy@glassy.jpl.nasa.gov
Date: Wed, 12 Oct 94 18:36:03 PDT
In case you're interested, there's a lot of information on
fluid dynamics software packages hidden among a
wide variety of finite element and fluid/heat packages
in the Sun Catalyst Software Catalog on the Web.
Solaris - Mechanical Engineering
Computational Fluid Dynamics
>From John R. Chawner /
mdaeng!jrc@uu4.psi.com
Date: Fri, 21 Oct 94 16:47:02 CDT
GRIDGEN is a software system for the generation of structured grids
for use in the computational sciences. The grids generated by
GRIDGEN consist of body-conforming, quadrilateral and hexahedral
cells. GRIDGEN is capability of building multi- or single-block
grids, abutting or overlapping blocks, surface or volume grids, and
2D or 3D grids. GRIDGEN consists of two codes, GRIDGEN (interactive)
and GRIDGEN3D (batch).
GRIDGEN is a visually oriented and interactive code in which user
control is maintained through menu button selection, mouse
point-and-click, and occasional text input. On-line help may be
accessed anywhere within the code, providing both specific and
general information to facilitate code usage. A User's Manual is
also available with sections covering the theory, how-to, and a
tutorial.
The GRIDGEN process begins with import of the geometry model about
which the grid is to be generated. The geometry model may be
imported in a variety of formats including NASA-IGES. Next, the user
interactively creates the curve, surface, and volume grid
components. Curves are constructed first as free space or
model-constrained curves of various mathematical forms. Grid points
are distributed along the curves using any of several clustering
functions that allow for clustering anywhere along the curve's
length. Surface grids are then initialized automatically after the
user selects the curves that define the surface's perimeter. Surface
grid point refinement may be achieved by applying a suite of
techniques from GRIDGEN's broad algebraic and elliptic partial
differential equation functionality. Volume grids are constructed in
a similar manner, by interactively selecting the surface grids that
comprise the block boundary. Volume grid points are initialized
automatically and may be refined by accessing GRIDGEN3D, a 3D partial
differential equation code run in batch mode.
Interfaces to the TEAM, NPARC, OVERFLOW, CNSFV, DTNS, and FANS
analysis codes are included in GRIDGEN. These interfaces allow users
to set solver-specific boundary conditions on the surfaces of the
blocks in the system. The final products of GRIDGEN, the grid and
connection/boundary condition input decks, can then be exported in
the exact form required by the flow solvers.
The GRIDGEN software consists of approximately 150,000 lines of
Fortran and C code, with all graphics implemented in Silicon
Graphics' IrisGL language. GRIDGEN runs on Silicon Graphics and IBM
RS/6000 workstations configured with the appropriate graphics
adapter, a 24-bit frame buffer, Z-buffer (recommended).
Now 10 years old and 300+ users strong, GRIDGEN development and
support today is maintained by its two original authors, John
Steinbrenner and John Chawner, of MDA Engineering, Inc., Arlington,
Texas. For information on how to obtain GRIDGEN and on GRIDGEN support
services please contact John Chawner at (817) 860-6660 or
gridgen@mdaeng.com for more information.
GRIDGEN is available at no cost from the U.S. Air
Force. Unfortunately, GRIDGEN is not available outside the U.S.
>From Charles Fletcher /
fletcher@nova.umd.edu
Date: Tue, 25 Oct 1994 15:54:39 -0400
N3S is a (commercial) finite element 2D/3D CFD code that runs on Unix
workstations, CRAY, and other supercomputers. N3S was developed by EDF
(France) and is distributed in the US by Scientific Services, Inc.
and in Europe by SIMULOG (France). N3S has both English and French versions.
For further information, please contact:
Charlie Fletcher
charlie@technosci.com
301-577-6000
or support@simulog.fr
Below is a summary of the software's (Release 3.1)
currently available offering:
Note: (*) = new capability of the release 3.1.
+ 2D - axisymmetric - 3D arbitrary complex geometries
+ laminar or turbulent flows and/or heat transfer
+ steady state and transient
+ incompressible flows
+ thermal energy equation
+ forced, free or mixed convection
+ conduction
(*) + expansible flows with high variations in temperature
+ 20 additional passive effluents
+ k-epsilon turbulence model
(*) + flows with temperature, space and time dependent properties
+ allowance for solid boundaries (friction, heat exchange)
+ time discretisation at first or second order in time for
laminar flows
+ time discretisation at first order in time for turbulent flows
(*) + space dependent time step
+ prescribed nodal values
+ prescribed general forces in momentum equation
+ prescribed general heat source in energy equation
+ prescribed general sources term in passive scalar
transport equations
+ prescribed general stress and flux
(*) + moving wall boundary conditions
(*) + multiple inlets and outlets
+ scalar and vectorised solvers
+ standard mesh generators: SIMAIL, I-DEASTM/CAEDS
+ standard post-processors: GRAFN3S, DATA VISUALIZER, TIGRE
+ full documentation including theoretical manual,
user manual and validation manual.
Optional turbomachinery module including:
(*) + flows in rotating reference frame
(*) + Coriolis forces
(*) + Vo component in axisymmetric problems
(*) + periodicity between non-parallel faces
Optional adaptive 2D meshing module
NEXT RELEASE 1995
Release 3.2 offering:
+ Low Reynolds Launder Sharma model
+ advanced wall laws for low Reynolds Model
+ Full Reynolds Stress turbulence model (2D isothermal)
+ finite volume convector for extra passive scalar
fields(2D laminar)
+ distributed head losses
+ porous media
+ conjugate heat transfer between fluids and walls
+ compressible 2D flows (subsonic and transonic) based on
fractional time step method
+ moving meshes
+ Solid-Fluid interactions
+ optional compressible N3S-MUSCL solver for subconic,
transonic and supersonic 3D flows
+ optional combustion module (PDF model)
+ improved user-interface on motif/X-Window environment
(file handling and program control through an interactive
mouse-driven graphical user-interface)
+ Lagrangian tracking model with:
- turbulent dispersion model (stochastic tracking procedure)
- wall particle interaction model
- coupling between the particles and the continuous phase
+ local refined ID modelling of boundary layers
+ time discretisation at second order in time for turbulent flows
+ Full Reynolds Stress turbulence model (3D, thermal coupling)
+ adapting 3D meshing
+ fully 3D free surfaces
+ radiative heat transfer
+ compressible 3D flows (subsonic and transonc) based on
fractional time step method
+ optional compressible N3S-MUSCL solver for subsonic,
transonic and supersonic 2D flows
+ finite volume convector for extra passive scalar fields(3D)
+ turbomachinery module: rotor-stator interactions
+ optional combustion module (PEUL model)
+ parallelized version
+ Eulerian computation of two-phase flows
+ Large-Eddy Simulation (LES)
+ binary flows (2 fluids of the same thermodynamic phase)
>From Murali /
mdamodaran@ntuvax.ntu.ac.sg
Date: Tue, 22 Nov 1994 10:22:08 +0700 (SST)
DIRECTORY OF CFD CODES ON IBM SUPERCOMPUTER ENVIRONMENT
=======================================================
Name: FLO27
Jameson, Princeton University
Brief Description:
FLO27 is a three-dimensional potential flow code that analyzes the
inviscid irrotational transonic flow around an airplane wing using the
finite volume scheme with sheared parabolic coordinates.
===========================================================================
Name: FLO28
Jameson, Princeton University
Brief Description:
FLO28 is a three-dimensional potential flow code that analyzes the
inviscid irrotational transonic flow around an airplane wing and
fuselage using the finite volume scheme with sheared parabolic
coordinates.
===========================================================================
Name: FLO36
Jameson, Princeton University
Brief Description:
FLO36 is a two-dimensional potential flow code that analyzes the
inviscid irrotational transonic flow around an airfoil by iterative
solution of the difference equations for the velocity potential. A
multigrid algorithm is used to accelerate convergence to a steady
state.
===========================================================================
Name: FLO52
Jameson, Princeton University
Brief Description:
This two-dimensional Euler code solves for the inviscid transonic
flow around an airfoil using the finite volume formulation.
Quadrilateral cells are used to subdivide the flowfield around the
airfoil and an O-mesh topology is used. Sample values of the flow
variables are stored at the center of each cell. Adaptive
dissipation is added for clean and crisp capturing of shock waves.
A multigrid algorithm is used to accelerate convergence to a steady
state. Conformal mapping is used for grid generation.
===========================================================================
Name: FLO53
Jameson, Princeton University
Brief Description:
This two-dimensional Euler code solves for the inviscid transonic
flow around an airfoil using the finite volume formulation.
Quadrilateral cells are used to subdivide the flowfield around
the airfoil and a C-mesh topology is used. Sample values of
the flow variables are stored at the center of each cell.
Adaptive dissipation is added for clean and crisp capturing
of shock waves. A multigrid algorithm is used to accelerate
convergence to a steady state. Conformal mapping is used for
grid generation.
===========================================================================
Name: FLO57
Jameson, Princeton University
Brief Description:
This three-dimensional Euler code analyzes the inviscid transonic
flow around an airplane wing using the finite volume formulation.
Hexahedral cells are used to subdivide the flowfield around
the wing and sample values of the flow variables are stored at
the center of each cell. Adaptive dissipation is added for
clean and crisp capturing of shock waves. A multigrid algorithm
accelerates convergence to a steady state. Conformal mapping is
used for grid generation.
===========================================================================
Name: FLO59
Jameson, Princeton University
Brief Description:
This three-dimensional Euler code analyzes the inviscid transonic
flow about an arbitrary wing/fuselage/tail/fin configuration using
the finite volume formulation. Hexahedral cells are used to
subdivide the flowfield around the wing and sample values of the
flow variables are stored at the center of each cell. Adaptive
dissipation is added for clean and crisp capturing of shock waves.
A multigrid algorithm accelerates convergence to a steady state.
Conformal mapping is used for grid generation.
==========================================================================
Name: FLO67
Jameson, Princeton University
Brief Description:
This three-dimensional Euler code analyzes the inviscid transonic
flow around an airplane wing using the finite volume formulation.
Hexahedral cells are used to subdivide the flowfield around
the wing and sample values of the flow variables are stored
at the vertices of each cell. Adaptive dissipation is added
for clean and crisp capturing of shock waves. A multigrid
algorithm accelerates convergence to a steady state. Conformal
mapping is used for grid generation.
==========================================================================
Name: FLO82
Jameson, Princeton University
Brief Description:
This two-dimensional Euler code supercedes FLO52. It analyzes
the inviscid transonic flow around an airfoil using the
finite volume formulation. Quadrilateral cells are used
to subdivide the flowfield around the airfoil and an O-mesh
topology is used. Sample values of the flow variables are stored
at the center of each cell. An improved treatment of adaptive
dissipation provides for better capturing of shock waves and
other discontinuities. A multigrid algorithm together with a
residual smoothing procedure provide rapid convergence to a steady
state. Conformal mapping is used for grid generation.
===========================================================================
Name: FLO83
Jameson, Princeton University
Brief Description:
This two-dimensional Euler code supercedes FLO53. It analyzes the
inviscid transonic flow around an airfoil using the finite volume
formulation. Quadrilateral cells are used to subdivide the
flowfield around the airfoil and a C-mesh topology is used.
Sample values of the flow variables are stored at the center of
each cell. An improved treatment of adaptive dissipation
provides for better capturing of shock waves and other
discontinuities. A multigrid algorithm together with a residual
smoothing procedure provide rapid convergence to a steady state.
Conformal mapping is used for grid generation.
===========================================================================
Name: FLO103
Jameson, Princeton University
Brief Description:
FLO103 is a two-dimensional Navier-Stokes code that solves for the
viscous transonic flow (both laminar and turbulent) around an airfoil
using the finite volume formulation. Quadrilateral cells are used
to subdivide the flowfield around the airfoil and a C-mesh topology
is used. Sample values of the flow variables are stored at the
center of each cell. An algebraic turbulence model is used for closure.
Adaptive dissipation is added for clean and crisp capturing of shock
waves. A multigrid algorithm is used to accelerate convergence to a
steady state.
This program may also be used to compute inviscid flows.
===========================================================================
Name: INS3D
D Kwak, NASA Ames Research Center
Brief Description:
INS3D is a three-dimensional Navier-Stokes code that analyzes the
viscous incompressible flow over arbitrary configurations. The flow
solver utilizes a pseudo-compressibility approach with an
approximate factorization scheme. An algebraic turbulence model is
used for turbulence closure.
===========================================================================
Name: ARC3D
Tom Pulliam, NASA Ames Research Center
Brief Description:
ARC3D is a three-dimensional Navier-Stokes code that analyzes the
viscous compressible flow over arbitrary configurations. The flow solver
uses the ADI (Alternate Direction Implicit) algorithm to solve
the Reynolds averaged Navier-Stokes equations cast in conservation
law form. Adaptive dissipation is added for capturing shock waves.
An algebraic eddy viscosity model is used for turbulence closure.
===========================================================================
Name: VSAERO
Analytical Methods Inc, NASA Langley Research Centre
Brief Description:
VSAERO is a computer program for calculating the non-linear aerodynamic
characteristics of arbitrary configurations in subsonic flow. Non-linear
effects of vortex separation and vortex/surface interaction are treated
in an iterative wake-shape calculation procedure, while the effects of
viscosity are treated in an iterative loop coupling potential flow and
integral boundary layer calculations. The program includes many useful
features, including an automatic panel generator, and is applicable to
fluid flow problems in aerospace, automotive and marine areas.
===========================================================================
Name: TAIR
Terry Holst, NASA Ames Research Center,USA
Brief Description:
TAIR is a two-dimensional potential flow code which analyzes the
inviscid, irrotational flow over arbitrary airfoils.
The flow solver uses a fast, fully implicit
algorithm to solve the conservative full-potential equation
for transonic flow. A grid generation module to establish a general,
body-fitted finite difference mesh is included.
===========================================================================
Name: FIDAP
Dr. Michael Engelman, Fluids Dynamics International, Inc.
1600 Orrington Avenue, Suite 400, Evanston, Illinois 60201
USA
Brief Description:
The Fluid Dynamics Analysis Package (FIDAP) is a general purpose
program that uses the finite element method to simulate many classes
of incompressible fluid flows. Two-dimensional, axisymmetric
or three-dimensional steady-state or transient simulations
in complex geometries are possible.
The following types of steady state or transient analysis are supported:
isothermal Newtonian or non-Newtonian flows; turbulent flows, free
forced, or mixed convection; advection-diffusion problems (velocity
field fixed in space and time); environmental flows; creeping flows
(such as molten glass or metals) and free surface flows.
===========================================================================
See also: VSAERO, FIDAP.
>From Andrzej Banas /
banasa@cu29.crl.aecl.ca
Date: Tue, 29 Nov 1994 10:52:46 -0500
TASCflow: a general purpose 3D fluid flow & heat transfer code
available from
Advanced Scientific Computing Ltd.
Waterloo,
Ontario, Canada
For more information see Cray Research catalogue.
Public
ftp
archive of the CFD Community Club at the Rutherford Appleton Laboratory.
FEMLAB group
Dep. of Mathematics
Chalmers University of Technology
Göteborg
Sweden
FEMLAB is an interactive program for the numerical solution
of ordinary and partial differential equations based on the
Finite Element Method in adaptive form with automatic error
control.
Femlab is distributed freely to anyone interested. You may
read more about FEMLAB
and find
what do you need to get FEMLAB running.
Finally, you may
download FEMLAB.
>From Dennis J. Kingsley /
kingsl_d@cockle.navsea.navy.mil
Date: Thu, 15 Dec 1994 07:08:13 -0500
SLAW
SAIC Annapolis MD, USA,
Contact Ken Weems / ken@moe.seatec.saic.com
PMARC
NASA PD version of VSAERO
Contact COSMIC, University of Georgia
email service@cossack.cosmic.uga.edu
SWIFT
CDNSWC Carderock MD, USA
Contact Yoon Kim / yhkim@oasys.dt.navy.mil
XYZFS
CDNSWC Carderock MD, USA
Contact Bill Cheng / bcheng@oasys.dt.navy.mil
OVERFLOW (RANS)
???
ISFLOW
???
DTRANS3D?
Developed by Dr. Joe Lin's group at CDNSWC Carderock MD, USA.
These cfd codes are used for ship design. SLAW, PMARC, SWIFT, and XYZFS
are Potential Flow solvers, and furthur SLAW, SWIFT, and XYZFS have a
free surface boundary condition.
>From Juliusz Kirejczyk /
Juliusz@ix.netcom.com.us
Date: Sat, 17 Dec 1994 20:33:04 -0800
FLOTRAN,
ANSYS, Inc.
finite element method, integrated with ANSYS pre/postprocessor
MarketIXComputational_Fluid_Dynamics_CFD
Eli L. Isaacson, Dan Marchesin, and Bradley J. Plohr
SUNY Department of Applied Mathematics and Statistics
The executable file "rp" contained in
the present directory
has been compiled on a SPARCstation 2. It requires OpenWindows 2.0 and the
Sun Fortran library to work.
The program "rp" is an interactive graphics program for
exploring systems of two quadratic conservation laws.
It includes the ability to construct:
integral curves
Hugoniot curves
wave curves (comprising rarefaction, shock,
and composite segments)
wave speed diagrams
bifurcation loci (including coincidence, inflection,
secondary bifurcation, and double sonic loci)
solutions of Riemann problems
*********************************************************************************
NOTICE: You are free to use this program for studying quadratic models
and formulating conjectures about their solutions. If this program
provides useful insight, please acknowledge its use in any relevant
publication.
*********************************************************************************
Access via ftp. Here is
an excerpt from
README file:
Downloaded from netlib2.cs.utk.edu; 2/24/94
# chammp
# ======
# This directory contains items relating to the numerical solution
# of the shallow water equations in spherical geometry.
# The shallow water equations are used as a kernel for both
# oceanic and atomospheric general circulation models and
# are of interest in evaluating numerical methods for weather
# forecasting and climate modeling. The DOE Computer Hardware,
# Advanced Mathematics and Model Physics (CHAMMP) program
# is interested in the development of new mathematical methods
# for these problems. To promote this developmet, a set of
# test cases has been proposed and example software and reference
# solutions are provided.
[snip]
>From Jonas T. Holdeman, Jr. /
hol@ornl.gov
Date: Tue, 07 Feb 1995 15:09:52 -0500
I am surprised you don't have any mention of the NACHOS II code by D. K.
Gartling of Sandia National Laboratory, Albuquerque, New Mexico 97185, USA.
I had no trouble obtaining a free copy. The code is documented in two
reports: "NACHOS II - A Finite Element Computer Program for Incompressible
Flow Problems, Part I - Theoretical Background (SAND86-1816 UC-32) and Part
II - User's Manual (SAND86-1817 UC-32). The code is written in Fortran. It
features triangular and quadrilateral elements, primative variables, with
post-processing for stream-function, fluid stress and flux computation.
I heard that Gartling was working on a 3D version of Nachos, but I don't
know for sure. There should be several other codes from Sandia.
Barry Merriman /
barry@starfire.ucsd.edu /
merriman@fusion.ucsd.edu
UCSD Fusion Energy Research Center
UCLA Dept. of Math
Distribution file is obtainable via
ftp.
Here is an excpert from FMS-1D doc/Manual/UserManual:
FMS (Fluid Modeling System) is a system for constructing and
numerically solving the kinds of equations that arise in
general fluid flow problems, i.e. systems of conservation
laws. The current version handles flows in one space
dimension, plus time. FMS is intended to be a flexible and
powerful general purpose tool for this type of modeling.
The user supplies FMS with a description of the spatial
domain, and the system of equations to be solved, including
any boundary conditions or initial conditions, and FMS
attempts to compute the the corresponding solution (steady
state or time dependant).
>From Brian Pospichal /
blpospic@cca.rockwell.com
Date: Thu, 16 Feb 1995 10:52:42 -0600
FLOTHERM:
FLOTHERM is designed to provide an analysis tool for all aspects of
thermal problems arising in electronic equipment.
It is particularly powerful in cases where convective cooling is
domonant or critical. It provides complete analysis of the flow of
cooling fluid (usually air) simultaneously with thermal analysis.
FLOTHERM handles thermal and fluid dynamic behavior for:
* 2D and 3D
* steady and transient
* laminar and turbulent
* forced and natural convection
* convection,conduction and (to an extent) radiation.
* conjugate heat transfer
FLOTHERM is based on techniques of CFD, specifically the
Finite Control Volume approach.
* It operates in cartesian coordinates
* Calculation is performed in a rectangular cuboid solution domain
* Solution requires calculation throughout the domain of the variables:
- fluid (air) velocities in the x, y and z directions (u,v and w)
- fluid static pressure (p)
- temperature of fluid and, if required, in solid regions (T)
The variables are in general functions of x,y and z, and time t.
FLOTHERM is available, commercially, from:
Corporate Headquarters-
Flomerics Limited
81 Bridge Road
Hampton Court
Surrey KT8 9HH
England
North American Office-
Flomerics Inc.
57 Main Street
Suite 201
Westborough, MA 01581
USA
>From James D. Freels /
fea@fea.rrd.ornl.gov
Date: Tue, 27 Sep 94 10:48 EDT
AKCESS.4CFD Computational Mechanics Corporation finite-element
& AKCESS.* 601 Concord St., Suite 116 implicit time step
Knoxville, TN. 37919-3382 template input of equations
>From CFD Lab /
cfdlab@nestor.engr.utk.edu
Date: 17 Feb 1995 16:25:48 GMT
Any one who is interested in computational mechanics and do not like to
write lengthy codes to get a solution should try the new AKCESS.* platform.
For a brief overview look into the WWW mosaic page at
http://cmc2.akcess.com/.
>From Ralph Jones /
jones@hap.arnold.af.mil
Date: Mon, 27 Feb 95 14:02:11 -0600
THE NPARC FLOW SIMULATOR
The NPARC code embodies the most recent, proven CFD technology
available. It is a general-purpose fluid flow simulator ideally suited
to applications which involve complex geometries. In the hands of a
fluid dynamist with a basic familiarity with CFD technology, the NPARC
code is a powerful tool for the analysis of many complex flows of
immediate interest.
GENERAL DESCRIPTION
The NPARC Navier-Stokes code is a general purpose computational fluid
dynamics (CFD) tool which is applicable to a wide variety of aerospace
design and analysis problems involving fluid flow. It is actively
supported by the NPARC Alliance, a partnership between the NASA Lewis
Research Center and the Arnold Engineering Development Center. This
Alliance seeks to enhance the military and commercial competitiveness
of the United States through the establishment of the NPARC code as a
national resource.
The NPARC flow simulation program is used to calculate the properties
of a fluid flow, based on specified boundary surfaces and flow
conditions. These boundary surfaces can be quite complex and the fluid
can be treated generally. Inviscid and viscous flows can be
calculated. Viscous flows can be laminar or turbulent and can be
treated as fully viscous or as shear layer flows. This computer
program may be used to simulate steady-state and transient flows. The
NPARC code, which is written in FORTRAN 77, is easily ported to most
computer architectures (e.g. SGI and IBM workstations, VAX
minicomputers, Cray and Convex supercomputers). It is robust and
fairly easy to use. Anyone who is familiar with computers and has a
basic understanding of the physics of fluid flows should have little
trouble learning how to apply the NPARC code.
NPARC code flow simulations have had a demonstrable impact on
aerospace propulsive applications as diverse as supersonic and
hypersonic inlet design, rocket nozzle failure analysis, and turbine
engine exhaust mixer design. This computer program has also proven
capable of treating many other aerodynamic problems, such as, missile
nose cone analysis, instrumentation probe design, and ducted flow
analysis.
TECHNICAL FEATURES
The principal distinguishing features of the NPARC flow simulation
software are its generality, flexible grid requirements, robustness,
and modeling versatility.
GENERALITY
The basis of the algorithms used in the NPARC code is the complete
Navier-Stokes equations in conservation law form. Various
specializations are provided. For example, the viscous terms can be
selectively calculated so that a thin-layer simulation can be
performed or an inviscid (Euler) flow-field calculated. Similarly, for
viscous simulations the fluid flow can be treated as laminar or
turbulent as desired.
GRID FLEXIBILITY
The principal distinguishing feature of the NPARC code is its
generalized treatment of boundary conditions. Physical and
computational boundaries may be located on any grid surface without
restriction. Any portion of any grid surface may be a boundary
surface. Common boundary conditions (e.g., slip and no-slip wall,
symmetry plane, free-stream) can easily be selected for each
boundary. These features allow complex geometries to be readily
treated using a single grid. Complex geometries may also be broken
into a number of grid blocks. Grid blocking circumvents computer
memory limitations, simplifies grid generation about complex
geometries and permits grid embedding techniques. Communication
between grid blocks is accomplished through the overlapping of
grids. Adjoining grid blocks do not need to have an exact match of
grid points.
ROBUSTNESS
The NPARC code is also very robust. A semiautomatic time-step control
feature allows flow simulations to proceed from nearly arbitrary
initial conditions with little danger of divergence. This is
accomplished by monitoring and limiting the maximum change in the flow
field between iterations. In steady-state calculations, the time-step
size is determined by stability considerations. An optimal time-step
size is used for each grid point, reducing the total number of
iterations to reach steady-state.
TURBULENCE MODELS
Another distinguishing feature of the NPARC code is its flexible
turbulence modeling capabilities. The general purpose algebraic
turbulence model, although optimized for free shear layers at moderate
Mach numbers, provides reasonable viscous effects for almost any
combination of shear layers. A standard Baldwin and Lomax algebraic
turbulence model is also provided as an option when maximum accuracy
is required in skin friction and heat transfer. When an algebraic
turbulence model is inappropriate, either a one-equation model
(Baldwin-Barth) or a two-equation model (Chien k-epsilon) may be used.
ALGORITHMS
Almost any flow idealization can be simulated: 2-D, axisymmetric, or
3-D; inviscid, laminar, or turbulent; steady state, or
transient. These flow simulations are calculated using either the
pentadiagonalized form of the Beam and Warming approximate
factorization algorithm or the Jameson multilevel scheme. The Beam and
Warming algorithm is an implicit, computationally robust scheme for
solving the Navier-Stokes equations. The most attractive feature of
the algorithm, as modified by Pulliam, is that it forms an ADI type of
scheme in which each sweep involves the inversion of a set of scalar
pentadiagonal matrices. The Jameson multilevel algorithm is
second-order accurate in time. It may be used in the form of a
three-, four- or five- stage scheme. The Beam and Warming algorithm
has the best convergence properties, while the Jameson scheme has the
best time-accuracy.
ACQUISITION
ELIGIBILITY AND ALLOWABLE USES
The NPARC Software is releasable to all US owned companies, public and
private Universities, and government agencies. However, only US
citizens and resident aliens may have access to the software. In
general requests from foreign owned, controlled, or influenced
(nonresident foreign nationals on the board of directors) corporations
will not be granted. AEDC will use the Defense Logistic Agency or the
Defense Investigative Service database to verify the ownership of the
corporation. Corporations or other entities not listed in these
databases will be considered on a case by case basis. The software may
be used for any purpose in the national interest. This includes
enhancing either the economic or military competitiveness of the
United States. It may not be used in a contract with a foreign
government. Other restrictions are detailed in the Memorandum of
Agreement form which must accompany a request for the software.
SOFTWARE RELEASE
In order to obtain a copy of the NPARC software and documentation, you
must fill out the appropriate Software Release Form. There are
separate forms for US GOVERNMENT and COMMERCIAL AND ACADEMIC
release. This form establishes a Memorandum of Agreement which is the
legal mechanism for releasing the NPARC Software to users. It is an
Arnold Engineering Development Center (AEDC) form used to release all
AEDC developed and/or managed software. The form may be typed or hand
written in ink. For copies of the Memorandum of Agreement forms and
instructions, see FOR MORE INFORMATION below.
Completed forms should be forwarded (via mail or FAX) to:
NPARC Support
Attn.: Dr. Kyle Cooper
1099 Avenue C
Arnold AS, TN 37389-9013 FAX: 615-454-6317
RECEIVING THE SOFTWARE
The software can be made available on a variety of mediums (e.g., 1/4
inch tape, 5 1/4 or 3 1/2 inch disk) or via electronic transfer. One
should expect to receive the software approximately two weeks after
AEDC receives the Memorandum of Agreement form.
FOR MORE INFORMATION
I you have any questions concerning NPARC capabilities
or acquisition (including requests for Memorandum of
Agreement forms and instructions), or the NPARC
Alliance, call 615-454-7455 (this number will connect
you to the NPARC Hotline at the Arnold Engineering
Development Center, Arnold Air Station, TN USA) or
send email to
nparc-support@info.arnold.af.mil.
Alternatively, you may contact the NPARC WWW home page
at http://info.arnold.af.mil/nparc/.
See also: MDAE.
Computational Mechanics Company,Inc. (COMCO).
Storesim/Tetmesh
a Multi-Body CFD Grid Generation and Flow Solution Software
Unisim
a Two-Phase Reservoir Simulator built using
PHLEX,
a multipurpose hp-adaptive, vector/parallel finite element kernel.
KASIMIR:
The program is commercially available from the
Shock Wave Laboratory. If
you need more information, please contact Michael Lenartz, e-mail
address: sysman@ernst.swl.rwth-aachen.de.
>From Douglas Stillman /
doug@osa.sci.jri.co.jp
Date: Tue, 28 Mar 95 14:14:21 +0900
The LS-DYNA3D program now has a finite element based Eulerian -
Arbitrary Lagrangian Eulerian capability. The method used is based on
a Van Leer advection scheme. The principle application is for
fluid-structure interaction problems or fluids problems with moving
boundary conditions.
The software is commercial and available from:
Livermore Software Technology Corporation - Japan Research Institute
Engineering Department, ISS-Bldg., 1-33-8, Shinmachi
Nishi-Ku, Osaka 550, Japan
Tel: 81 6 536-7631 Fax: 81 6 532-9701
E-Mail: doug@osa.sci.jri.co.jp
>From Stephen Kramer /
kramer@bones.et.byu.edu
Date: Mon, 27 Mar 1995 13:27:58 -0700
The Advanced Combustion Engineering Research Center's (ACERC):
advanced combustion codes for entrained flows and fixed beds.
ACERC is a National Science Foundation (NSF) sponsored center which
specializes in comprehensive combustion code development. PCGC-2 and
PCGC-3 (Pulverized Coal Gasification or Combustion, 2 or 3
dimensional) are comprehensive CFD codes that treat coal
devolatilization and combustion, gas phase reactions, flow and
turbulence, and heat transfer- convective, conductive, and radiative.
They have been used to simulate full-scale commercial boilers as well
as laboratory-scale reactors. They can be used for non-reactive
simulations, gas-phase only simulations, particle dispersion
simulations, as well as comprehensive combustion simulations. Special
features include advanced NOx formation subroutines, a host of
particle reaction subroutines, SOx generation and sorbent interaction,
and advanced radiation and turbulence models. Current efforts
include: the application to premixed, turbulent flames, specifically
gas turbines; inclusion of various gridding techniques; slagging and
fouling; refinements to various submodels; and more predictions of
commercal furnaces. Reaction Engineering International (REI) codes
were based on versions of these codes. The current distribution
policy allows older versions (2yrs?) to be public domain, and the
newer versions to be available for something like a $30,000 membership
fee. Also available is FBED-1, a fixed-bed reaction code.
People to contact for information are
Scott Hill
(scotty@byu.edu)
head of the Combustion Computations Laboratory and responsible for
PCGC-3 code development,
Scott Brewster
(brewster@guitar.et.byu.edu)
person responsible for advanced turbine code development, and
Andy Eaton
(ame@homer.et.byu.edu),
person responsible for industrial interaction and support on code issues.
Mike Radulovic
(ptr@homer.et.byu.edu) is
responsible for FBED-1 development.
Please contact them for the official information concerning these codes.
>From Marc Tombroff /
num@stro10.vub.ac.be
15 rue Dautzenberg
1050 Brussels
Belgium
Tel: +32/(02)6292378
Fax: +32/(02)6292880
NUMECA International s.a.
NUMECA is presently offering the following software:
- IGG (Grid Generation): IGG is a powerful Geometry Modeller and
Grid Generation system for creating high quality multiblocs strucutred
meshes around complex geometries.
- EURANUSturbo (Flow Simulation): EURANUSturbo is a powerful
numerical simulator, tuned to the simulation of 3-D Reynolds-averaged
Navier-Stokes internal flows.
- CFView (Interactive 3D Visualization): CFView is an Interactive
Computational Field Visualization system for general structural or CFD
analysis.
- FINEturbo (Integrated Environment): FINEturbo is a user-friendly
CFD environment, combining IGG, EURANUS/TURBO and CFView, and dedicated to
Turbomachinery applications.
For more information:
link to NUMECA.
CEI Inc. /
ensight@ceintl.com
PO Box 14306
Research Triangle Park, NC 27709 USA
tel: (919) 481-4301
fax: (919) 481-4306
EnSight is
an advanced CFD postprocessing package with a unique distibuted
architecture. For more information, CEI, Inc. or ensight@ceintl.com.
NA Digest Sunday, May 21, 1995 Volume 95 : Issue 21
>From Xiaolin Li /
xli@cs.iupui.edu
Date: Mon, 15 May 1995 10:29:12 +0500
Subject: Software for 3-D Fluid Interfaces Available
Software for simulating the 3-D fluid interface instabilities in
compressible fluids (Rayleigh-Taylor and Richymyer-Meshkov instabilities)
is available to those who are interested in applying it to scieitific
problems.
This code uses a resolution enhanced numerical scheme for contact
surface, that is, the second order TVD with artificial compression
(TVD/AC). The fluid contact interface is traced through the level set
method. The code has both the seriel and parallel modes and can be
run in parallel and distributed system such as the iPSC-860 and the PVM.
The output features the triangulated surface which can be viewed
by using the geomview software package.
For detail and to obtain this code, please send email to:
xlli@silver.ucs.indiana.edu.
Tomasz Plewa /
tomek@MPA-Garching.MPG.DE /
plewa@sirius.astrouw.edu.pl