DTIC ADA505953: NAVO MSRC Navigator. Fall 2006

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NAVO MSRC Navigator. Fall 2006
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(MSRC),1002 Balch Boulevard,Stennis Space Center,MS,39522
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As this issue of the Navigator goes to press, be the maintenance of a premier HPC
we're fielding the most capable HPC environment with the support you have
systems ever installed at the NAVO MSRC. come to expect from all of the centers.
Our two new IBM POWER5+ HPC systems, To this end, the NAVO MSRC has been
BABBAGE and PASCAL, have performed asked by the HPCMP to lead a collaborative
well in their factory predeployment testing effort with the other centers and industry to
and look to be outstanding performers in completely reengineer and modernize the
the future. As icing on this tasty cake, we're
fielding them in a newly renovated,
New HPC Systems,
physically hardened facility with the
necessary resilience to sustain 24 x 7
More, to Serve
operations in Mother Nature's worst weather
or even with major computer facility support
You Better
equipment failure.
In addition, we are working with NASA to
establish resilient, multi-gigabit, northbound
communications service for Stennis Space data storage environment and capabilities
Center which will further improve across the entire program. This will be a
the operational availability of the NAVO huge effort with the potential to dramatically
MSRC for the nationwide DoD HPCMP improve the technical capabilities, cost-
user community. effectiveness, and usability of the HPC
systems themselves and their associated
We have also been actively participating in
data storage/management environments.
the planning for the consolidated customer
I am extremely excited by this project and
assistance and visualization environments
very pleased that we have been asked to
for the six centers within the HPCMP, all of
participate in it.
which have received preliminary approval
and endorsement by the HPCMP Corporate As always, we solicit your constructive
Board of Directors. As I mentioned in the criticism of the NAVO MSRC and invite you
last issue, please be assured that our to let us continue to assist you in bringing
primary goal throughout this budget this cutting-edge capability to bear in
adjustment and consolidation process will support of your HPC needs.
2 FALL 2006 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
Defense (DoD) scientists and engineers with high The Director’s Corner
performance computing (HPC) resources,
including leading edge computational systems, 2 New HPC Systems, More, to Serve You Better
large-scale data storage and archiving, scientific
visualization resources and training, and expertise
Feature Articles
in specific computational technology areas (CTAs).
These CTAs include Computational Fluid
Dynamics (CFD), Climate/Weather/Ocean 4 Mock Disaster Successful at the Disaster Recovery
Modeling and Simulation (CWO), Environmental Facility
Quality Modeling and Simulation (EQM),
Computational Electromagnetic and Acoustics 5 Hypersonic Scramjet Technology Enhancements for
(CEA), and Signal/Image Processing (SIP).
Long Range Interceptor Missile
NAVO MSRC 9 High-Performance Computing Tools Enable Army
Code N7 Survivability and Lethality Technology Development
1002 Balch Boulevard
13 Validation and Installation of LSF on Large IBM AIX
Stennis Space Center, MS 39522
Clusters
1-800-993-7677 or
[email protected] 15 The Remote Visualization Resource Manager
16 CFD Simulation of Flow and Dispersion in Complex
Buildings
The Porthole
22 Visitors to the Naval Oceanographic Office
Major Shared Resource Center
NAVO MSRC Navigator
www.navo.hpc.mil/Navigator
Navigator Tools and Tips
NAVO MSRC Navigator is a biannual technical 29 Running X Windows with Parallel Codes on KRAKEN
publication designed to inform users of the news,
events, people, accomplishments, and activities of Under Platform Computing's Load Sharing Facility
the Center. For a free subscription or to make
address changes, contact NAVO MSRC at the Upcoming Events
above address.
31 Coming Events
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 FALL 2006 3
Mock Disaster Successful at the Disaster Recovery Facility
Edward Farrar, NAVOMSRC Systems Administration
BACKGROUND of the DRAT. Once the HPCMO selected the the site for
the DR facility, the DRAT was charged with developing a
In today's rapidly evolving, high-technology world,
system to store and protect the data in the DR Facility
knowledge is power and data is knowledge. Protecting
(DRF) and to create a process to recover the data within
data, particularly in the post 9/11 world, and maintaining
five days of a disaster at any participating site. The DRAT
continuity of operations are priorities for both businesses
then quickly laid the groundwork for a DR system to
and governments. The High Performance Computing
protect HPCMP data from across the program.
Modernization Office (HPCMO) and its components have
embraced meeting this protection challenge. Currently, all sites are sending data to the DR facility. The
facility now stores nearly three Petabytes of data and has
The HPCMO recognizes that data are its most valuable
been operational since November 2004. The storage
product–and the easiest to protect. In 2003, the HPCMO
growth of the DR is shown in Figure 1. The validity of the
commissioned Instrumental, Inc., to perform a study on
DR and its data storage system was proven in a recent
the storage infrastructures at all the Major Shared Resource
Mock Disaster Test coordinated and overseen by the
Centers (MSRC) and several of the Distributed Centers
NAVO MSRC.
(DC). The study found an array of solutions for protecting
data, that most sites had multiple copies of data, and that
EVOLUTION OF THE DISASTER RECOVERY FACILITY
only one site had started creating an off-site copy of data
for Disaster Recovery (DR) purposes. In March 2004, the DRAT built consensus on DR goals and
initiated the system design process. The basic design
In October 2003, the Disaster Recovery Advisory Team
concept used the remote disk archiving feature of SAM-
(DRAT) was created with Instrumental, Inc., as the facilitator.
QFS. The DR conceptual design is depicted in Figure 2.
Representatives from the Army Research Laboratory (ARL)
Remote disk archiving allows each participating site to
MSRC, Aeronautics System Center (ASC) MSRC, Engineer
create a duplicate data archive set that would be physically
Research and Development Center (ERDC) MSRC, Naval
stored at the DRF. Supplemental recovery information is
Oceanographic Office (NAVO) MSRC, Arctic Region
also collected at the DRF. This choice meant that a
Supercomputing Center (ARSC) DC, Maui High Performance
Computing Center (MHPCC) DC, and the Defense
Research and Engineering Network (DREN) are members Continued Page 25
3,500
3,000
2,500
)
B
T 2,000
(
e
g
a
r 1,500
o
t
S
1,000
500
0
MAR 06 MAY JUL SEP NOV JAN 06 MAR MAY JUL
Figure 1.DRF storage growth.
4 FALL2006 NAVO MSRC NAVIGATOR
Hypersonic Scramjet Technology Enhancements
for Long Range Interceptor Missile
S.M. Dash, A. Hosangadi, R.J. Ungewitter, J.D. Ott, and K.W. Brinckman, Combustion Research and Flow Technology, Inc.,
Pipersville, PA and K. Kennedy, Army Missile Research Development and Engineering Center, Redstone Arsenal, AL
INTRODUCTION LENS shock tunnel facility. CFD has This paper first describes the CFD
proven invaluable in the interpretation codes used for scramjet design and
The Army has been involved in the
of scramjet data, in providing component optimization followed by a
development of a new hypersonic
performance parameters not available description of the modeling used in
missile that is rocket boosted and
from testing (i.e., combustion the codes–including an overview of
scramjet propelled. Scramjet air
efficiency),and in shedding insight
how large eddy simulation is
breathing propulsive systems are
into the complex physics occurring
implemented to calibrate the
highly integrated with the missile
along the propulsive flowpath, which
advanced RANS turbulence models
using aerodynamic surfaces to is often highly nonlinear (i.e., small
being used.
compress the captured airstream changes often produce large effects).
before it enters the combustor. Some aspects of scramjet component
Via the use of the Naval Oceanographic
evaluation is also discussed as well as
Hypersonic scramjets, operating at Office Major Shared Resource Center
the approach used for design
high Mach numbers, use hydrogen as (NAVO MSRC) massive parallel
optimization using an evolutionary
the primary fuel, and there are many hardware platforms and CFD codes
algorithm. In performing optimization
complex flowpath design issues that configured to perform efficiently on
studies, a series of cases are performed
must be addressed that include these platforms, end-to-end Reynolds
concurrently at each design level,
transitional turbulence, shock/boundary Average Navier-Stokes (RANS) solutions
which for fuel injector optimization
layer interactions, fuel/air mixing in a with resolved grids can now be obtained
has required very substantive resources.
highly compressible environment, and in several days. This is extremely
ignition/flameholding for operation at encouraging as the implementation CODES UTILIZED
higher altitudes. of advanced thermo-chemical and
An overview of the CFD and grid
Computational Fluid Dynamics (CFD) turbulence/transitional models requires
adaptation codes utilized for scramjet
has played a major role in overall the integration of a very large system
calculations is provided in Table 1. For
design and scramjet component of coupled partial differential
optimization performed in conjunction equations with widely disparate
with full-scale experiments in the length/time-scales. Continued Next Page...
CCRRAAFFTT CCFFDD®® CCooddee CCRRUUNNCCHH CCFFDD®® CCooddee CCRRIISSPP®® GGrriidd AAddaappttaattiioonn CCOODDEE
SSttrruuccttuurreedd GGrriidd NNSS//RRAANNSS//PPNNSS MMuullttii-- MMuullttii--EElleemmeenntt,, UUnnssttrruuccttuurreedd GGrriidd OOppeerraatteess oonn MMuullttii--EElleemmeenntt ((hheexx,, tteett,,
BBlloocckk SSoollvveerr NNSS//RRAANNSS CCooddee pprriissmm,, eettcc..)) GGrriiddss ffoorr VVaarriieedd UUNNSS CCooddeess
AAddvvaanncceedd TThheerrmmoo--CChheemmiiccaall,, MMuullttii-- SSiimmiillaarr FFeeaattuurreess aass iinn CCRRAAFFTT CCFFDD®®CCooddee AAddaappttss ttoo GGrriidd QQuuaalliittyy aanndd FFllooww
PPhhaassee,, && TTuurrbbuulleennccee MMooddeellss FFeeaattuurreess ffoorr BBootthh SStteeaaddyy aanndd
DDyynnmmaammiicc FFlloowwss
IInn OOppeerraattiioonn ffoorr OOvveerr 1155 YYeeaarrss IInn OOppeerraattiioonn ffoorr OOvveerr 1100 YYeeaarrss AAuuttoommaatteedd IInntteerrppoollaattiioonn ttoo nneeww GGrriidd
&& RReebbaallaanncciinngg ooff LLooaaddss
SSppeecciiaalliizzeedd FFeeaattuurreess ffoorr SSccrraammjjeett UUsseedd ffoorr FFllooww RReeggiioonnss RReeqquuiirriinngg HHiigghh OOppeerraatteess oonn MMuullttii--EElleemmeenntt ((hheexx,, tteett,,
AApppplliiccaattiioonnss ssuucchh aass TTrraannssiittiioonnaall RReessoolluuttiioonn ((ttrriippss,, FFuueell IInnjjeeccttoorrss,, eettcc..)) pprriissmm,, ----)) GGrriiddss ffoorr VVaarriieedd UUNNSS CCooddeess
TTuurrbbuullaannccee MMooddeellss,, TTrraannssppiirraattiioonn WWaallll && ffoorr CCoommpplleexx DDeessiiggnnss ((ii..ee..,, IInnwwaarrdd
BBCC,, && MMuullttii--PPhhaassee DDrroopplleett//PPaarrttiiccllee TTuurrnniinngg SSccrraammjjeettss
CCaappaabbiilliittiieess ffoorr AAlltteerrnnaattee FFuueellss
Table 1.Codes Utilized for Scramjet Applications.
NAVO MSRC NAVIGATOR FALL 2006 5
conventional rectangular designs (e.g., Use of conventional, cell-splitting Using dynamic load balancing, based
NASP, Hyper-X), a hybrid approach is adaptation can lead to a large on work per node,1has led to
utilized, with the structured grid increase in the number of nodes (see effective load balancing in such
numerics in the CRAFT CFD® code the table in Figure 1–which shows an situations and is being supplemented
applied for most of the flowfield, but increase from 7 million (M) to 13.5M by use of tabulated procedures (In
with the Unstructured Navier-Stokes cells in Pass 1–which did provide a Situ Adaptive Tabularization (ISAT),
(UNS) numerics of the CRUNCH grid resolved solution since Pass 2 Artificial Neural Network (ANN), etc.).
CFD® code required where fine-scale results were essentially identical). The The fuel injection region of combustors
features must be resolved–such as in authors have been working on hybrid can be very Central Processing Unit
the vicinity of transition trips on the cell splitting/cell stretching adaptation (CPU) intensive, particularly for
forebody and in the fuel injector concepts, which remedy this issue but problems where ignition kinetics is
regions of the combustor. still require further development to required, requiring 10-15M cells and
Several levels of grid adaptation are resolve “tangling issues.” solving 20 or more coupled Partial
often required for which the CRISP Differential Equations (pde's)(five gas
While conventional load balancing
CFD®code is utilized. Figure 1 shows dynamic, nine or more chemical
(same number of cells per domain)
product formation contours at several species, and eight turbulent/transition
using domain decomposition with MPI
stations in the elliptical combustor of a equations–further discussed in the
generic inward-turning scramjet, is effective for aerodynamic problems, Models Utilized section). Analysis of
where fuel is injected from the walls it is problematic for scramjet combustor this region takes about three-quarters
using flush, angled injectors. problems where varied zones in the of the overall CPU time (including
flow have differing work loads. Using
The combustion efficiency (obtained grid adaptation), and full end-to-end
with the original and adapted UNS iterative matrix-split chemical kinetic runs on 256-512 processors are
grids) indicates that unless the grid is techniques, it is possible that 100 routinely performed in several days.
adapted, this efficiency is overestimated iterations per CFD time-step in fuel
(due to numerical diffusion effects). injection regions may be performed MODELS UTILIZED
Since there is only half-plane symmetry, (where ignition reactions have small The modeling utilized in performing
the fuel/air mixing details for multiple time-scales), and minimal iterations in scramjet simulations is summarized in
injectors must be resolved. other regions. Table 2. Basic models are used for
Combustion Efficiency
y Original
c
n
e
ci
Effi Adapted
Length
Original Adapted Pass 1 Adapted Pass 2
Number ofVenticies 1,848,643 2,456,536 2,830,591
Number ofTetrahedral Cells 5,955,505 10,011,954 12,413,432
Number ofHexahedral Cells 603,801 603,801 603,801
Number ofPrism Cells 406,866 406,866 406,866
Figure 1.Grid adaption effects on combustion efficiency and grid size.
6 FALL 2006 NAVO MSRC NAVIGATOR
preliminary design and to expedite the development and has required some fluctuation data in high speed flows.
early stages of design optimization. “local” modifications to the source However, Large-Eddy Simulation
Advanced models are used for terms used in the low Reynolds (LES) solutions of unit fuel injection
interpreting experimental data and for Number turbulence models. problems are providing supportive
refining designs. Transitional models, Scalar fluctuation modeling is playing data. Figure 3 shows one such LES
which solve pde's for onset location a dominant role in obtaining accurate solution with contours of time-averaged
and for intermittency (i.e., three values for fuel/air mixing. The turbulent mean flow (u, T, YH2) and
dimensional blending from laminar to pde's implemented solve the corresponding Root Mean Squared
turbulent flow), have been calibrated temperature/energy and species (RMS) fluctuations exhibited.
for hypersonic flows and compared variance and related dissipation rates This case represented Hydrogen
with varied shock tunnel data sets. and are used to obtain local values of angled fuel injection into a high speed
These models take into account the turbulent Prandtl (Prt) and Schmidt airstream to emulate the environment
fluctuation in acoustic noise levels in (Sct) numbers that govern thermal in a high Mach combustor. RANS
test facilities (prescribed as inflow and species turbulent diffusion. Most comparisons were quite reasonable,
condition) and are extremely useful in CFD codes require specification of and values of Turbulent PrtNumber
suggesting boundary layer trip location constant values for these parameters, and Sctand Lewis Number (Le) (=
modifications in going from full-scale but their values in fuel injection regions Prt/Sct) varied substantially in the
testing to a quieter flight environment. can vary substantially as shown by the injector region.
Analysis techniques for the transitional Sct contours in Figure 2.
flow downstream of trips using the Calibration and validation of these STUDIESSUPPORTINGSYSTEMDESIGN
intermittency model is still in models suffer from lack of scalar Earlier studies have been performed
for rectangular scramjet designs, with
interdigitated flush and wedge
Schmidt Number Contours
injectors,2to assess the ability of the
CFD codes shown in Table 1 to
Sc
t
26 1.2 reproduce data obtained in varied
1.1 Large Energy National Shock Tunnel
20 0
0.9
0.8
15 0.7
0.6 Continued Next Page...
10 0.5
0.4
0.3
05 0.2
0.1
0 0 Figure 2.Schmidt number contours
-40 -20 0 20 40 –fuel injection in high speed
X/b
stream.
MMooddeelliinngg BBAASSIICC AADDVVAANNCCEEDD
TTrraannssiittiioonnaall MMooddeellss CCaalliibbrraatteedd AAllggeebbrraaiicc PPDDEEss ffoorr PPrreeddiiccttiinngg OOnnsseett//33DD
OOnnsseett//IInntteerrmmiitttteennccyy MMooddeellss IInntteerrmmiitttteennccyy
TTuurrbbuulleennccee MMooddeellss UUnniiffiieedd KKeewwiitthh EExxtteennssiioonnss EEAASSMM NNoonn--LLiinneeaarr MMooddeell
GGrriidd AAddaappttiioonn SSiinnggllee PPaassss,, tteett//pprriissmm//hheexx,, hh-- MMuullttii--PPaassss,, tteett//pprriissmm//hheexx rr//hh HHyybbrriidd
RReeffiinneemmeenntt ((cceellll sspplliittttiinngg)) RReeffiinneemmeenntt
TTuurrbbuulleenntt SSccaallaarr TTrraannssppoorrtt CCoonnssttaanntt//ZZoonnaall PPrrtt99,, SScctt LLooccaall VVaalluueess ffrroomm PPDDEEss
TThheerrmmoo--CChheemmiiccaall NNoonneeqquuiilliibbrriiuumm ffoorr SSttaannddaarrdd//EExxtteennddeedd MMeecchhaanniissmmss wwiitthh PPDDFF TTuurrbbuulleenntt CCoommbbuussttiioonn MMooddeell,,
CCoommbbuussttiioonn aanndd HHyyppeerrssoonniiccss IIggnniittiioonn && AAiirr RReeaaccttiioonnss VViibbrraattiioonnaall NNoonneeqquuiilliibbrriiuumm
FFllooww PPaatthh DDeessiiggnn TTrriiaall && EErrrroorr GGeenneettiicc,, MMuullttii--VVaarriiaattee DDeessiiggnn
OOppttiimmiizzaattiioonn
Table 2.Basic and advanced models used for scramjet applications.
NAVO MSRC NAVIGATOR FALL 2006 7
(LENS) tests performed at full-scale combustionefficiency in a reasonable
and for duplicated flight conditions. length is a design concern.
These studies highlighted the need to A basic issue is that of fuel injector
In
dsgcreiadvle aalrod fpalu pactadtutviaoatnnio cinne d mf utoerald niensljsiet icaotnnodra lrt eoag niuodsnes. ward Turning ssspthoaoiccwihnnigo i mnw eFittihrgy us taruend d5ie .i snU jfseoicnrt gofi rxa es sdizm ef uaaelslel/rair
The conclusion from these varied number of injectors provides good
comparative studies was that CFD penetration, but air passes between
could provide very reasonable injectors, while using a larger number
cwwreohismtoheuproearu crstei tsirsogo nnwnsiegt iwr oebin tuuh ra sndiediadnst g.at o Nou cAnsucdVupeOrprr oecModrtnS adRitCions Concept Flowpath oatwhnfoi dsirn k pujeerndecbtl iobumrersisn,nt t,ar eabrsyiuru tsli tnttsuh dtiehny e s,p o tcoeleuonntr it oirnpnajeel niccset ooftrarrears.t iIonn
substantive number of end-to-end from optimal.
comparative studies and were key to
the progress made in generating Figure 4.Inward turning model and FUEL INJECTOR OPTIMIZATION
accurate solutions in a timely manner. flowpath. To optimize fuel injector patterns/
Of most recent interest in this Army/ conditions to yield the highest
NAVO MSRC work are inward-turning 4. Such propulsive flowpaths are now combustion efficiency for a fixed
concepts (utilizing a “sugar-scoop” being integrated into hypersonic combustor length, multi-variate
inlet) that compress the flow in a missile designs, and numerous CFD genetic-based optimization3is being
shock-free manner into an elliptical calculations have been performed in used, with a schematic of the Graphical
support of systems studies.
combustor with flush, angled injectors. User Interface (GUI)-driven framework
This flowpath is very difficult to implemented shown in Figure 6.
These concepts have been tested in
the Calspan-University of Buffalo calculate,and UNS numerics are used The genetic optimization procedure
Research Center (CUBRC) LENS for the entire end-to-end calculation.
facility with an inlet section and While on-design inlet performance is
numerical model as shown in Figure generallyquite good, achieving good Continued Page 24...
1
.75
.5
.25
Injectors
0
Figure 3.LES simulation of fuel injection flowfield.
8 FALL 2006 NAVO MSRC NAVIGATOR
High-Performance Computing Tools Enable Army
Survivability and Lethality Technology Development
Stephen J. Schraml and Kent D. Kimsey, U.S. Army Research Laboratory
Sean Ziegeler, Visualization Software Engineer, NAVO MSRC VADIC
Physics-based simulations, when of advanced survivability and lethality tens of millions of processor hours of
utilized on High Performance technologies. Possibly the most notable usage each year on HPC resources
Computing (HPC) systems, can be use of numerical simulations in this deployed under the DoD High
used to develop and assess lethality development process is parametric Performance Computing
and survivability technologies. Examples analysis. Once a numerical model of a Modernization Program (HPCMP).
of these for Army applications include particular weapon-target interaction is CTH uses a two-step solution scheme
penetrators, warheads, explosives, developed and the bounds on the –a Lagrangian step followed by a
passive and active armors, and armor parameters of interest are defined, remap (or advection) step. The
materials for equipment and personnel. numerous simulations can be performed conservation equations are replaced
Large-scale numerical simulations of to determine how each parameter's by the explicit finite-volume equations
complex weapon-target interactions variation influences the performance solved in the Lagrangian step. The
help guide experiments, illustrate of the system under study. remap step uses operator-splitting
physical processes, ascertain techniques to replace multidimensional
performance limits, extract transient COMPUTATIONAL METHODOLOGY equations with a set of one-dimensional
response characteristics, and augment The computational methodology that equations.2
experimental databases. This article is commonly used in modeling High-resolution material interface
provides an overview of the complex weapon-target interactions trackers are available to minimize
computational terminal ballistics is the shock physics code CTH.1 material dispersion. Analytical and
methods that are used on HPC CTH is an Eulerian finite-volume tabular equations of state are available
resources at the Naval Oceanographic code for modeling solid dynamics to model hydrodynamic behavior or
Office Major Shared Resource Center problems that involve shock wave materials. A variety of constitutive
(NAVO MSRC) by researchers at the propagation, multiple materials, and models are available to treat elastic-
U.S. Army Research Laboratory (ARL). large deformations in one, two, and plastic material behavior. Models for
The evolution of scalable HPC systems, three dimensions. explosive detonation are also available
along with recent advances in CTH is widely used across the to handle the reactions of energetic
continuum mechanics codes, has defense research and development materials.
enabled large-scale simulations to play community to model problems in
a paramount role in the development shock wave propagation resulting in Continued Next Page...
Figure 1.CTH mesh decomposition with explicit message passing.
NAVO MSRC NAVIGATOR FALL 2006 9