SGI Origin2000 CAE ????????

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SGI Origin2000 CAE ????????

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• ??SGI????
• tomuro_at_sgi.com
• All material SGI ProprietarySubject to change
  without notice

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CAE????????????
??????????????? (CC-NUMA) ????????????
Origin Server 1 - 128 R10000s 256 GB memory
Onyx2 Visualization 1 - 128 R10000s 256 GB
memory
Octane Workstation 1 - 2 R10000s 2 GB
memory

• CAE??????????? ?????????
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• ??I/O - ??????I/O??????
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Origin2000 - I/O??
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• Origin2000 I/O ??
• Fiber Channel ??????
• 4.3 GB/s??????????????
• 3.9 GB/s??????????????
• 7.6 GB??????????1??????
• SCSI ??????
• 1 TB ???????1?????
• 1 TB ??????????152??????
• 3.8 GB/s??????????????
• 2.0 GB/s??????????????
• 7.2 GB??????????1??????

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CAE????????

• CAE????????
• ?????????
• MSC/NASTRAN?ABAQUS?MARC??
• ??????????????????????????????????????????????????
  ???????????????????????????
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• LS-DYNA?STAR-CD?FLUENT??
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FEA???????

• ??FEA???????????
• ??FEA????????????????????

1968
1978
1988
1998
Application
MSC/NASTRAN (1963) ANSYS (1970) Pro/MECHANICA
(1987) MARC (1966) ABAQUS (1978) ADINA (1986)
skyline
sparse
iterative
frontal
sparse
skyline
sparse
iterative
skyline
iterative
sparse
frontal
sparse
skyline
sparse
iterative
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FEA???????????

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Solver Type Operations Implementation Profile D
OF 20 ?? Sparse ! DOF 3 ?? Desktop
FEA 25K DOF 250K DOF (????????)
2
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FEA????????
??????????????????????????????????????????????????
???????????
??FEM??
Matrix Assembly
Matrix Assembly
?????
Solver (Sparse)
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Recover Stresses
?????
Solver (Profile)
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Recover Stresses
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??????????????

• ???????CAE????????
• ???FEA MARC
• ???FEA RADIOSS?PAM-CRASH?LS-DYNA??
• CFD STAR-HPC?FLUENT/UNS?CFX5??

System
?????????? ??????????????????????????????????????
??MPI???????????????????
CPU1 CPU2 CPU3 CPU4
3
2
image
4
1
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??????????????

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• ?????????CFD???????????FEA??????????????

• CFD?????????????????????????????????????
• FEA????????????????????????????????????????????

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??????CFD
Origin CC-NUMA ????? SMP(?????), ?????
DMP(?????)
CFD Software Discretization Parallel
Strategy Commercial FLUENT Structured SMP, fine
grain STAR-CD Unstructured SMP, fine
grain CFX4 Structured MB SMP, fine or
coarse STAR-HPC Unstructured DMP, message
passing FLUENT/UNS Unstructured DMP, message
passing RAMPANT Unstructured DMP, message
passing CFX5 Unstructured DMP, message
passing Research OVERFLOW Structured,
overset SMP, coarse STAR-CD Structured MB DMP,
message passing NSMB (Europe) Structured MB DMP,
message passing FLO107 (Jameson) Structured
MB DMP, message passing FEFLO (Lohner) Unstructure
d SMP, coarse
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??????CAE
Software FLUENT/UNS CFD Model Underhood/external
aero, 3D, K-E incompressible, iso-thermal, 1M
cells
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??????CAE
Software FLUENT/UNS CFD Model External aero,
3D, incompressible, iso-thermal, k-e, 11M cells
NOTES Cells 11,710,641 / Faces 23,908,997 /
Nodes 2,202,149 / Memory 9000 MB
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??????CAE
Software START-HPC 3050 CFD Model Underhood/exte
rnal aero, 3D k-e, compressible, 3.1M
cells Solve Strategy Single prec, simple,
vector, MPI
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CAE????????
Stanford University/NASA Aerodynamics Research,
Prof. Jameson
Sample Simulation SYN107-MB Design optimization
study of a fullconfiguration supersonic transport
Benefits - From Baseline to Optimized in 20
min on SU Origin2000 - Optimized for desired
separation and shock strength/location -
Simulation necessary for algorithm theory behind
optimization
Time Required for Solution
Model Description 185 blocks, 1.7M grid
points, inviscid Euler, 526 iters per design
step, 4 steps
SYN107-MB 2.1
Origin20001 cpu 51727
Origin2000 16 cpu 2005
Origin2000 32 cpu 1046
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CAE????????

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??????CAE
NASA Ames Research Center
??? OVERFLOW ????????747???????
?? - NASA??????????????????128???????????????????
? - ??????????????
Origin2000 Performance - GFLOPs Overflow Origin
2000 Origin 200 Cray C90 64 cpu 256 cpu 16
cpu 1.7 10.1 20.1 4.6
Model Description
33M grid points, 153grid zone,
turbulent,compressible, 10 iters
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??????CAE
Software RAMPANT CFD Model External aero,
compressible, k-e , 500K cells
British Aerospace 3D Wing Aerodynamics
Hardware Origin 2000 128p, 16Gb memory
Notes Cells 473,293 / Faces867,829 /
Nodes117,448 / Memory500 MB
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CFD??????????
CFD?????????Origin??????
Company British Aerospace General
Motors Chrysler Ferrari (ITL) Mercedes-Benz Ar
nold Engineering Development Corp Volvo (SWE)
CFD Software RAMPANT STAR-HPC FLUENT/UNS FLUEN
T/UNS START-HPC GASP FLUENT/UNS
Scaling 50x - 64p 24x - 30p 60x - 64p 50x -
60p 40x - 50p 89x - 128p 129x - 120p
Model/Cells (M) Ext Areo/ 0.5M Und Hood/
1.1M Und Hood/ 1.1M Und Hood/ 2.1M Und Hood/
2.8M Ext Areo/ 10.4M Ext Areo/ 11.2M
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CFD??????????
SMP????????????????????????
Source Why HP for Fluent?, 1998 Users Group
Presentation, 4 x V2200 Cluster, FLUENT/UNS
4.2.5, HyperFabric System Interconnect
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LS-DYNA?????
Software LS-DYNA 940 FEA Model 86,000 element
frontal car crash simulation Solve
Strategy Single prec, MPI
Num. of Seconds Speed up Speed up

PE (Wallclock) (every 2
fold)
2 232,430 ---- 2.00
4 103,090 2.25 4.50
8 47,776 2.15 9.72
16 25,230 1.89 18.42
32 14,147 1.78 32.84
64 9,552 1.48 48.67
96 7,217 ---- 64.41
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LS-DYNA?????
LS-DYNA Performance Trends

• Origin wins recent 2 Gigaflop Crash Challenge
• NCAC Neon Model Front crash,271K elements
• 150 msec simulations (5ms run)
• System CPUs 5ms TIme Speed-Up MFlops
• CRAY C90 1 8865 1.0 185
• Origin 30 1028 8.6 1590
• 48 746 11.9 2190
• 64 697 12.7 2350

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??????CAE
BMW Body Engineering
???????? PAM-CRASH Origin2000 ???????????????
SGI Hardware Environment 500 CPUs ???Origin2000

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• ???????????????????? 750K ???
• 250K?????1M??????????????
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??????CAE
BMW 50km/s frontal crash 52,216 elements, 35000
contact segments of type 36 V96D PVM based on
Origin2000/195MHz
Speedup
CPUs
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