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1. REPORT DATE 3. DATES COVERED
2008 2. REPORT TYPE 00-00-2008 to 00-00-2008
4. TITLE AND SUBTITLE 5a. CONTRACT NUMBER
NAVO MSRC Navigator. Spring 2008
5b. GRANT NUMBER
5c. PROGRAM ELEMENT NUMBER
6. AUTHOR(S) 5d. PROJECT NUMBER
5e. TASK NUMBER
5f. WORK UNIT NUMBER
7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION
Naval Oceanographic Office (NAVO),Major Shared Resource Center REPORT NUMBER
(MSRC),1002 Balch Boulevard,Stennis Space Center,MS,39522
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unclassified unclassified unclassified Report (SAR)
Standard Form 298 (Rev. 8-98)
Prescribed by ANSI Std Z39-18
BBBBeeeehhhhindddd tttthhhheeee CCCCuuuurrrrttttaaaaiiiinnnn
An opportunity for NAVO MSRC senior staff to reflect on the NAVO MSRC’s past, present, and future endeavors.
As we approach the summer of 2008 the Although the MSRC still resides physically
NAVO MSRC is flush with change and growth. in the Naval Oceanographic Office
For the first time in three years the Center will (NAVOCEANO) buildings, in May 2007
once again feature CRAY technology along the Center moved organizationally to
with its powerful, reliable arsenal of IBM Power NAVOCEANO’s parent command, the Naval
platforms. Our Technology Insertion 2008 (TI- Meteorology and Oceanography Command
08) enhancements–an IBM P6 and a CRAY XT5 (COMNAVMETOCCOM). And, for the first time
cluster–will quadruple the amount of computing
capability we provide to our users. You will find
more details on these systems on page 17 of this Amidst a Year of
issue of The Navigator.
Changes, NAVO MSRC
Considerable infrastructure enhancements are
currently being undertaken in two facilities
Remains Focused
to accommodate the CRAY XT5, the water-
cooled IBM P6, and their counterpart test and
development systems. Our Sun F12000 mass
Christine Cuicchi
storage servers JULES and VINCENT will be
Computational Science and Applications Lead,
replaced with a single Sun M5000 server within NAVO MSRC
this calendar year.
We will also be bringing SL8500 technology
in nearly eight years, the Center is bringing
for our Disaster Recovery (DR) capabilities
aboard new government staff to enhance and
to accommodate the growth of other High
broaden our expertise.
Performance Computing Modernization
During this time of growth and transition
Program (HPCMP) centers’ data holdings. With
the award of the HPCMP’s Next Generation we remain dedicated to providing reliable
Technical Services contract to Lockheed Martin computational capabilities and exceptional,
(the incumbent contractor at NAVO MSRC) we innovative service to our users and to the
look forward to embracing the new cooperative Program. We’re excited about our future and
opportunities among our sister centers. your part in it.
22 SPRING 2008 NAVO MSRC NAVIGATOR
Contents
The Naval Oceanographic Office (NAVO)
Major Shared Resource Center (MSRC):
Delivering Science to the Warfighter
The NAVO MSRC provides Department of NAVO MSRC Update
Defense (DoD) scientists and engineers with high
performance computing (HPC) resources, including
leading edge computational systems, large-scale 2 Amidst a Year of Changes, NAVO MSRC Remains Focused
data storage and archiving, scientific visualization
resources and training, and expertise in specific Feature Articles
computational technology areas (CTAs). These
CTAs include Computational Fluid Dynamics
5 Hypersonic Continuum/DSMC Methodology for Steady/
(CFD), Climate/Weather/Ocean Modeling and
Simulation (CWO), Environmental Quality Transient Missile and Re-Entry Vehicle Flowfields
Modeling and Simulation (EQM), Computational
Electromagnetic and Acoustics (CEA), and Signal/ 9 Using ParaView for Remote Visualization on IBM AIX
Image Processing (SIP).
12 Global and Mesoscale Ensemble Forecasts of Tropical Cyclones
NAVO MSRC 17 EINSTEIN and DAVINCI Come to the MSRC
Code 0TC
1002 Balch Boulevard The Porthole
Stennis Space Center, MS 39522
1-800-993-7677 or 19 Visitors to the Naval Oceanographic Office
[email protected] Major Shared Resource Center
Navigator Tools and Tips
21 Top 5 Frequently Asked Questions about $HOME and
$WORKDIR on the NAVO MSRC High Performance
Computing Systems
NAVO MSRC Navigator
Upcoming Events
www.navo.hpc.mil/Navigator
23 Coming Events
NAVO MSRC Navigator is a biannual technical
publication designed to inform users of the news,
events, people, accomplishments, and activities
of the Center. For a free subscription or to make
address changes, contact NAVO MSRC at the
above address.
EDITOR:
Gioia Furness Petro, [email protected]
DESIGNERS:
Kerry Townson, [email protected]
Lynn Yott, [email protected]
Any opinions, conclusions, or recommendations
in this publication are those of the author(s) and
do not necessarily reflect those of the Navy or
NAVO MSRC. All brand names and product
names are trademarks or registered trademarks
of their respective holders. These names are for
information purposes only and do not imply
endorsement by the Navy or NAVO MSRC.
Approved for Public Release
Distribution Unlimited
NAVO MSRC NAVIGATOR SPRING 2008 3
Hypersonic Continuum/DSMC Methodology
for Steady/Transient Missile and Re-Entry
Vehicle Flowfields
J.L. Papp, R.G. Wilmoth, D.B. VanGilder, and S.M. Dash, Combustion Research and Flow Technology, Inc.
K. Kennedy, U.S. Army Aviation and Missile Research, Development, and Engineering Center
IntroductIon breakdown surface is one-way, with
Higher-altitude missile and re-entry the continuum solution providing
DSMC
Analysis vehicle flowfield simulations often inflow boundary conditions for the
require the unification of continuum DSMC solution. For more complex
Navier-
Stokes Computational Fluid Dynamics (CFD) problems with multiple nozzles or large
Analysis and Direct Simulation Monte Carlo angles-of-attack, coupling can be two-
(DSMC) methodology. way and thus more complicated.
Plume Induced
Separation For missiles with propulsive plumes For RV or aerocapture flowfield
(as well as for missiles or Re-entry problems at moderate altitudes (50-
(a)
Vehicles (RVs) with divert/control jets), 70 km), the situation is reversed, with
the overall flow is rarefied at altitudes the flow being largely continuum
above 65-75 kilometers (km), requiring with embedded rarefied flow in the
ckLayer RarefieNda vAifetre-rSbtoodkye/sW Aankaelysis ttcthhooee na tup ibnslureuem uaomekf dD (oforSwro MmdnCi vst uehmrretfe /acntcohoenoz zwtdrlesoh. l oe Hjsxeeiott) we pixsela tveanen ert, atsFhcfotheer e rummbsoeiasd tsoiyizlf/ee wDd oa SirknM eR FCrVie g gmupiorreeont hb 1tolh(edbamo)t. ls or ewgqyiu,t hiar ess
Shom APbalrattiicvuel aGtaess/ DSMC Analysis iass btahsaet dfo ornm uralaretefadc tbioyn B cirrdit.e1r iHone nscuec,h dgeivoemrte/ctroinestr ocal nje tbse, bcroemakpdleoxw, nw hsuicrhfa ce
u
un RCS Jet a hybrid approach is required for has led to our development of
itnoC coupling the continuum and DSMC more advanced techniques for
solutions along the breakdown surface,
their construction in an Automated
as schematized in Figure 1(a), for a
(b) Efficient Generalized Interface Surface
conventional rocket plume.
(AEGIS) Toolkit.
For basic missile/plume problems, the
Figure 1. Examples of embedded
continuum to DSMC coupling at the
continuum/rarefied flow fields. Continued Next Page...
(e)
(d)
(a)
(c)
(b) (f) Comparison to image constraint
Figure 2. Demonstration of surface generation using GDM methodology within AEGIS toolkit for RCS thruster.
NAVO MSRC NAVIGATOR SPRING 2008 5
Extensions to unsteady problems (forcing function) parameters, to
using hybrid methodology (such produce a continuous and water-tight
as transient jets or bursts at high triangulated surface.
altitudes) require the construction of
The procedure can be thought of as a
time-varying breakdown methodology.
balloon expanding within a cage. As
Many problems of interest deal with
the balloon is inflated (deformation),
plumes or divert/control jets from solid
it gradually takes on the shape of (a)
propellant motors that can contain
the cage while the surface elasticity
relatively high loadings of particulates,
(topology) of the balloon prevents
such as Al2O3.
it from leaking out between any of
While the continuum plume codes
the bars.
contain well-established methodology
Eventually, a point is reached where
for the fully-coupled analysis of
the surface cannot expand without
particulates using either Eulerian
or Lagrangian numerics,2 DSMC violating any of the constraints and
(b)
codes do not and thus have required the process is complete. So, even
upgrades for particulate capabilities. though the image function may
be discontinuous, smoothness is
The DSMC code utilized for our
maintained as a constraint, and
studies is called Plume DSMC Analysis
an appropriate coupling boundary
Code (PDAC).3 PDAC is an extended
surface can be obtained from an
version of the DSMC Analysis Code
oftentimes complex field function.
(DAC)4 with particulate and unsteady
upgrades, as well as upgrades for An example of the image identification
plume thermo-chemistry. and surface generation process is
shown in Figure 2. The process begins (c)
AEGIS MEthodoloGy by choosing an appropriate image
Figure 4. Snapshots of interface
The AEGIS Toolkit employs constraint (Figure 2a) that will define surface deformation using GDM
Geometrically Deformed Model the location of breakdown, which can component of AEGIS toolkit.
(GDM) methodology, which be the Bird breakdown parameter1 or
implements a cost minimization similar variable.
algorithm based on image The GDM process begins by
(breakdown parameter), topology introducing a seed surface within
(surface elasticity), and deformation the image constraint (Figure 2b).
(a)
(b)
(c)
(b)
(d)
(a)
Figure 5. Expansion of second
interface surface into far-field
Figure 3. Estimated breakdown surface for multi-nozzle plume. region.
66 SPRING 2008 NNAAVVOO MMSSRRCC NNAAVVIIGGAATTOORR
Through the deformation process, the as described in the previous section.
initial seed surface grows until it is The details of such flowfield solutions
constrained by the image (Figures 2c are available in a number of papers
through 2e). Comparison of the final presented at American Institute of
surface to the image constraint (Figure Aeronautics and Astronautics (AIAA)
2f) shows that the fit is quite good. meetings over the past several
The capabilities of the AEGIS years.3,5 A missile divert jet calculation
Toolkit are further demonstrated by is shown in Figure 7a with the
generating an interface surface for breakdown surface used for
a more complex multi-nozzle plume continuum/DSMC coupling shown
(Figure 3). AEGIS integrates the Gnu in Figure 7b.
Triangulated Surface (GTS) toolkit for A hybrid solution for an Apollo-like
computational geometry, and GTS is vehicle during re-entry is shown in
available as freeware. Figures 8a and 8b. The continuum
Two GDM surfaces are seeded and region is solved using the CRAFT
(a) Temperature Contours grown as seen in Figure 4. The near- CFD® code while the rarefied wake
field surface is then processed through region is solved using PDAC. As can
the GTS Boolean operator to stitch it be seen, there is very good continuity
to the nozzles (Figure 5). The resulting across the breakdown surface interface.
near-field surface is then merged
Results for an extension of the Apollo
to the far-field surface (Figure 6) to
re-entry hybrid simulation to three-
produce the final interface surface
dimensions are shown in Figures
ready for interpolation and conversion
9a and 9b. Here, three-dimensional
to an appropriate DSMC boundary
effects occur due to angle of attack,
format.
as well from the Reaction Control
System (RCS) thrusters. For this
hybrId SolutIonS for
case, the embedded rarefied wake
StEAdy flowS
region, for which a DAC simulation is
A variety of flowfields have needed, contains an embedded highly
been analyzed using the hybrid
dense RCS thruster core flow.
(b) Breakdown Surface methodology developed (with
coupling making use of breakdown
Figure 7. Hybrid solution for missile surfaces constructed using AEGIS) Continued Next Page...
divert jet problem.
(a) (c) (e)
(b) (d) (f)
Figure 6. GTS Boolean operations on GDM generated surfaces.
NNAAVVOO MMSSRRCC NNAAVVIIGGAATTOORR SPRING 2008 7
The versatility of AEGIS allows for the expanding domain problems have
generation of both the outer interface been examined.
Continuum Simulation
as well as the inner interface.
PArtIclE ExtEnSIonS
unStEAdy hybrId MEthodoloGy Lagrangian methodology used in
Extending hybrid methodology to our continuum codes2 has also been
unsteady flows, where the breakdown implemented in the PDAC DSMC
surface itself may vary with time and code. Figure 11 shows an application
where coupling conditions are also of methodology for a hybrid CFD/
transient, has been a challenge. The DSMC missile plume simulation.
first step has entailed development In a one-way coupled Lagrangian
of an unsteady version of PDAC that approach, the particle paths and
incorporates ensemble averaging of temperatures are determined by using
the flowfield properties at discrete calibrated drag and heat transfer
time intervals. correlations to account for momentum v(t)
and energy transfer from the gas to Time History at
Specified Location
Unsteady boundary conditions have Based on Breakdown Criteria
the particulates. PDAC uses identical
also been added to PDAC, which t
correlations to those used in the
also permits interpolation of a time-
continuum methodologies but also
varying source and/or wall boundary uses the same enthalpy-temperature
conditions in a more general manner curve fits and emissivity tables as the
icTmonofh o noeedta riibdncfioehueru ud ontm oftd o tachc prooeyeud srpceomol.eu ni trtd coteiitm iaponern o vuipannerpsirtauteitteai oswd nyoa ns cpccFohooaanurr tntpliiacgnlilreneugs guep mt bhopoa acousroectnidc cdaueleanrs rd.msy Te.r aaahsmdissi laleaotslialvsodleywi npsag rctoshr,op ese sr ttyh e yFreodtstioHaes U nsteadyBoundaryCCoMnSdDitiootn
all surfaces. Figure 10 schematizes significant energy and momentum miT
unsteady coupling methodology may be transferred from the solid
particulates back to the gas during
on a time-invariant surface with
the plume expansion, and treatment
time-varying conditions. A variety DSMC Simulation
of these problems requires a fully-
of fundamental cases illustrating
coupled approach.
application of this methodology
Figure 10. Hybrid transient
to high altitude transient jet
Continued Page 18 coupling.
8
(a) Temperature Contours
6
CRAFT-CFD (b) Close-up of RCS interface
Temperature 8 region showing surface elements
Contours
and number density contours
y4
Coupling
2 Boundary CRAFT-CFD
DAC97 AxCiaoln Vtoeulorcsity
0
0 2 4 6 8 (a) Temperature contours for
x 4 hybrid RCS simulation
y BCoouunpdlianrgy
2
DAC97
(b) Axial Velocity Contours 0
0 2 4 6 8
Figure 9. Apollo-like vehicle re-entry simulation at
Figure 8. Apollo-like vehicle simulation. angle of attack with dual thrusters.
8 SPRING 2008 NAVO MSRC NAVIGATOR
Using ParaView for Remote Visualization
on IBM AIX
Sean Ziegeler, HPCMP PET Enabling Technologies On-Site, Mississippi State University
Introduction Engineer Research and Development BABBAGE system. Executables
ParaView is an open-source Center (ERDC) Major Shared for the serial version of ParaView
application for viewing and analyzing Resource Center (MSRC) Data are located in /site/unsupported/
a wide variety of data sets. The major Analysis and Assessment Center paraview/serial/bin/. Executables for
capabilities of ParaView include: (DAAC) wiki page on ParaView the parallel Message Passing Interface
(https://visualization.hpc.mil/wiki/ (MPI) version (currently experimental)
•Support for two-dimensional (2D),
ParaView) for an introduction and of ParaView are located in /site/
three-dimensional (3D), and time-
tutorials on ParaView in general. unsupported/paraview/mpi/bin/.
varying data sets.
•Support for structured and Prerequisites Client-Server Mode ParaView
unstructured grids.
For this article, we will be using ParaView's client-server mode
•Available for many platforms ParaView 3.2.1. If the user does not operates, for the most part,
including Windows, Linux, have this version of ParaView, pre- transparently to the user. Except for
and Mac. compiled versions can be obtained for some initial configuration (which is
•A client-only mode for running on Windows, Linux, and Mac at http:// described elsewhere in this article),
a local desktop or laptop system. www.paraview.org/New/download. using ParaView in this way will be just
html. Users with other platforms like using it on the user's local system
•A client-server mode for
will have to compile the software (i.e., in client-only mode).
connecting a local system to a
server on a remote system. themselves. This article assumes that the user is a
Instructions for compiling ParaView beginner, but the user is nonetheless
•A parallel server mode for large
can be obtained at http://paraview. encouraged to become familiar with
data sets.
org/Wiki/ParaView:Build_And_Install. the basic operation of ParaView in
ParaView has many specific features
Fortunately for users of the Naval client-only mode, which, in fact, runs
that are beyond the scope of this
Oceanographic Office Major Shared a default server on any user's local
article. For more information
Resource Center (NAVO MSRC) system (Figure 1).
visit http://www.paraview.org/ for
ParaView is already installed on the In client-server mode, the user starts
background information and the
the ParaView server program on a
remote system (e.g., BABBAGE, in
this case). The user still runs the client
on the local system, but that client
now connects to the remote server
process, as shown in Figure 2.
Secure Shell (SSH) Port
Forwarding
In cases where the remote system is
behind a firewall, is an inaccessible
node on a cluster, or when network
traffic should be encrypted, Secure
Shell (SSH) port forwarding must
be used. This is the case with
BABBAGE’s compute nodes. This
means that the ParaView client
connects to SSH, which “tunnels” the
Figure 1. (Top) ParaView in client-only mode, running a default server. traffic through its connection and
Figure 2. (Bottom) ParaView in client-server mode between the local
system and a remote one. Continued Next Page...
NAVO MSRC NAVIGATOR SPRING 2008 9
