JAXA Supercomputer System Annual Report April 2017-March 2018

Convergence Acceleration with Hyperbolic Navier-Stokes Equations
Report Number：R17ECMP01
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4426/
Responsible Representative
Takashi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Atsushi Hashimoto hashimoto.atsushi@jaxa.jp

Members
Atsushi Hashimoto, Tsukasa Nagao

Abstract
We evaluate the hyperbolic equations for Navier-Stokes equations.
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-15K18286/

Reasons for using of JSS2
We plan a large scale computation in the future.

Achievements of the Year
We studied a laminar flow over a flat plate. (Fig. 1) shows the drag coefficient convergence. We
confirmed that the drag computed with the hyperbolic system converges more rapidly than that with thetraditional system. (Fig. 2) shows the residual of the streamwise velocity, u, versus the number of
iterations and CPU time. A comparison of the CPU time shows that the time for hyperbolic equations
is approximately 75% less than that for traditional equations.

Fig.1 Drag coefficient convergence

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.2 Residual versus number of iterations and CPU time

Publications
 Non peer-reviewed papers
1) Nagao, et. al., "A Study on Time Evolution Method for Hyperbolic Navier-Stokes System," AIAA
SciTech 2018, AIAA 2018-0370.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

N/A

Number of Processes

1

Elapsed Time per Case

1.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.00
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

0.00

0.00

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

000.52

0.00

/data

488.28

0.01

/ltmp

097.660.01

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Investigation on Fine-scale Scalar Mixing in High Reynolds Number Turbulent Jets
Report Number：R17ECMP02
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4427/
Responsible Representative
Takashi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Shingo Matsuyama smatsu@chofu.jaxa.jp

Members
Shingo Matsuyama

Abstract
In this research, large scale direct numerical simulation of turbulent flow is performed onsupercomputer to clarify the role of very small-scale turbulence in the mixing process of fuel and air. We
try to clarify the role of fine-scale turbulence by analyzing the data obtained by simulations with varying
the Reynolds number which is a parameter that governs the turbulence intensity.
https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-15K05817/

Reasons for using of JSS2
In order to clarify the role of fine-scale turbulence in scalar mixing process, statistical data by DNS is
required for high Reynolds number condition. For performing DNS under high Reynolds number
condition of Re > 104, a numerical mesh of the order of one billion points is required. Such large-scale
simulation can be executed only on a supercomputer, and therefore, supercomputer system is
indispensable for carrying out this research.

Achievements of the Year
DNSs were performed for turbulent planar jets at Re = 3×103, 104 and 3×104 on 0.1billion to 1.3
billion grid points with 9-th order spatial accuracy. It was confirmed by comparison with pastexperimental data and evaluation of Kolmogorov length scale that Re-dependence of planar jet iscorrectly reproduced by the present DNS (Fig.1). By filtering DNS data, it is found that the contribution
to turbulent scalar mixing due to turbulence with scales less than 60 and 100 times of kolmogrov lengthscale are negligible at Re = 3 ×103 and 104, respectively.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Instantaneous contours of scalar dissipation rate on the x-y plane (z = 0) for
the DNS at Re = 3×103,104 and 3×104 (from top to bottom). Cited fromnon peer-reviewed paper [2].

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.2 Movie of scalar dissipation rate for the DNS at Re = 3×103.

Fig.3 Movie of scalar dissipation rate for the DNS at Re = 104.

Fig.4 Movie of scalar dissipation rate for the DNS at Re = 3×104.

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Non peer-reviewed papers
1) Shingo Matsuyama, "Direct Numerical Simulation of a Turbulent Plane Jet with Scalar Mixing",
proceedings of the 48th JSASS annual meeting, 2C15, 2017.
2) Shingo Matsuyama, "DNS of a Turbulent Plane Jet with Scalar Mixing", proceedings of the JSFM
Annual Meeting 2017, 2017.
 Presentations
1) Shingo Matsuyama, "Direct Numerical Simulation of a Turbulent Plane Jet with Scalar Mixing", the48th JSASS annual meeting, 2017.
2) Shingo Matsuyama, "DNS of a Turbulent Plane Jet with Scalar Mixing", the JSFM Annual Meeting
2017, 2017.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

286 - 924

Elapsed Time per Case

1,000.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 2.67
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

22,602,550.63

3.00

SORA-PP

0.00

0.00

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

598.94

0.41

/data

2,849.03

0.05

/ltmp

488.280.04

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Adbanced Numerical Simulation of Compressible Two-phase Flow of diesel atomization
Report Number：R17ECMP04
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4428/
Responsible Representative
Takuji Kurotaki, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Takuji Kurotraki kurotaki@chofu.jaxa.jp

Members
Takuji Kurotaki

Abstract
Atomization of fuel of aeronautical engines is focused in because of fuel consumption andenvironmental issues. Information from CFD results is very helpful for solutions of them. The researchof numerical simulation of compressible muti fluid flow is conducted to apply for these problems.
Reasons for using of JSS2
Super computer system can be used from simple problems for the validation of basic method torelatively large application for unsteady and multi dimensional problems. It is convenient for the speed
up of development of numerical cord.
This kinds of simulation deal with unsteady problems and in order for the reduction of computationaltime, the ability of handling of parallel computing is indispensable.

Achievements of the Year
Two main approach to the simulation of compressible multiphase flow are investigated; diffuse
interface approach which treats the interface as mixture of both fluids and sharp interface approach withlevelset method.
In the development of diffuse interface approach, basic equations are extended to six equation modeland by considering the chemical equilibrium it became to possible to treat phase change such as
cavitation. Atomization of fuel from 2D nozzle is simurated by this chords.
In the development of sharp interface approach, new HLLC scheme which is extended to treat phasechange models at the interface and it was confirmed that the problem of the cavitation collapse are
simulated accurately and the methods to inprove the mass prezervation was investigated.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Volume fraction of fuel and numerical Schlieren

Fig.2 Volume fraction of vapor of fuel and air

Publications
 Presentations
1) Sumi, Kurotaki,' Ubsteady Numerical Simulation of Compressible Gas-Liquid Two-Phase Flow for
Ultra-High-Pressure Fuel Injection,'The 28th Internal Conbustion Symposium (2017), 13.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

10.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.00
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

4,466.74

0.06

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

005.09

0.00

/data

078.01

0.00

/ltmp

1,041.67

0.08

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Post-K Priority Issue 8D: Research and development of core technology to innovate
aircraft design and operation
Report Number：R17ECMP06
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4429/
Responsible Representative
Yuko Inatomi, Institute of Space and Astronautical Science, Department of Interdisciplinary Space
Science

Contact Information
Ryoji Takaki ryo@isas.jaxa.jp

Members
Ryoji Takaki, Taku Nonomura, Seiji Tsutsumi, Yuma Fukushima, Soshi Kawai, Yuki Kawaguchi,
Ikuo Miyoshi, Satoshi Sekimoto, Shibata Hisaichi, Hiroshi Koizumi, Yuichi Kuya,
Tomohide Inari, Ryota Hirashima

Abstract
We develop a high-speed/high-precision computational program using a quasi-first principle method,which can faithfully reproduce the actual flight environment to understand the true nature of fluid
phenomena. Specifically, we develop a high-precision compressible flow solver with geometric wallmodels and LES (Large Eddy Simulation) wall models based on hierarchical, orthogonal and equally
spaced structured grids.

Reasons for using of JSS2
We need large computer like JSS2 because our calculations must be large scale computations. Moreover,
JSS2 has a similar architecture to the our target computer called Post-K.

Achievements of the Year
We advance the development of FFV-HC-ACE: a compressible Navier-Stokes equation solver using
hierarchical, orthogonal and equally spaced structured grid. Following new functions are added to theprogram; calculation function of convective and viscous fluxes using image point (IP) and data
communication function between oblique blocks. A flow around a NACA0012 2D airfoil is calculated asa preliminary validation of the program. Fig. 1 shows the Mach number distributions around the airfoil
and block boundaries. Mach number is 0.3, Reynolds number is 10,000 and attack angle is 3 degree.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Mach number distributions around NACA0012 (Mach number is 0.3, Reynolds
number is 10,000 and attack angle is 3 degree)

Publications
 Presentations
1) H. Shibata, M. Sato, Y. Fukushima, S. Tsutsumi, T. Nonomura, S. Kawai and R. Takaki,
Development of a compressible flow solver using hierarchical Cartesian grids - toward the age of
Exa-scale supercomputers-, 29th international conference on parallel computational fluid dynamics.
2) H. Shibata, M. Sato, S. Tsutsumi, Y. Fukushima, T. Nonomura, S. Kawai and R. Takaki,
Investigation of flux based wall boundary condition for hierarchical cartesian grid method, 49th
Fluid Dynamics Conference/35th Aerospace Numerical Simulation Symposium.
3) H. Shibata, Y. Fukushima, S. Tsutsumi, Y. Kuya, S. Kawai and R. Takaki, Assessment of wallboundary conditions for a cartesian grid method, 31th Computational Fluid Dynamics Symposium.
4) R. Takaki, Characterization of PRIMEHPC FX100 by CFD solver using structured grid method, 1stWorkshop of HPC MONOZUKURI on Post-K

Priority Issue 6 6 and 8.

5) R. Takaki, A challenge to analysis of real complicated configurations of aircraft -Sub-issue D-, 1stWorkshop of HPC MONOZUKURI on Post-K

Priority Issue 6 6 and 8.

6) R.Takaki, Characterization of many core CPU by CFD programs, 49th Fluid Dynamics
Conference/35th Aerospace Numerical Simulation Symposium.
7) R. Takaki, H. Shibata, S. Kawai, Y. Fukushima, S. Tsutsumi and Y. Kuya, A challenge to analysis ofreal flight Reynolds number flows by Post-K computer, 55th Aircraft Symposium.

JAXA Supercomputer System Annual Report April 2017-March 20188) R. Takaki, High performance computing by many-core based CPU, 3rd Symposium on Space
Science Informatics.
9) R. Takaki,

Toward the achievement of the aerodynamic characteristic evaluation for realconfigurations and real flight environments of aircraft, 3rd Symposium on Post-K computer Priority
Issue 8.

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

2 - 20Elapsed Time per Case

20.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.76
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

6,186,602.05

0.81

SORA-PP

759.840.01

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

3,310.17

2.29

/data

21,116.11

0.39

/ltmp

10,782.88

0.81

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

38.98

1.68

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Small synthetic aperture radar satellite
Report Number：R17ECMP07
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4430/
Responsible Representative
Takahiro Yamada, Institute of Space and Astronautical Science, Division of Spacecraft Engineering

Contact Information
Tomoya Fukami fukami.tomoya@ac.jaxa.jp

Members
Tomoya Fukami, Hirobumi Saito, Kengo Ando, Pyne Budhaditya, Prilando Rizki Akbar

Abstract
We are goint to develop synthetic aperture radar system that can be onboard on a 100kg class satellite
and to verify it on ground. Conventionally radar observations have required large or medium satellitewith 500-1000kg mass. Our research and development may change earth observation drastically.
http://www.jst.go.jp/impact/en/program/13.html

Reasons for using of JSS2
We utilize super-computer for design of slot array antennas dedicated for small synthetic aperture radar.
Design of slot array antenna requires a super-computer that is provided with high speed and large
memory.

Achievements of the YearWe performed simulation for 4 panels antenna and antenna network feeder system for antenna panels
array. Here the, we simplified the simulation of network feeder system for 7 antenna panels array with
3.5 antenna panels array simulation. The simulation results are shown in Fig.1. In this simulation, inphase and uniform excitation to the parallel-plate antenna are expected. Furthermore, the simulation
results which are showing performance of each antenna panels is shown in Fig.2.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Tournament feeder network design for 7 antenna panels array.

Fig.2 Antenna Panels simulation results.

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Peer-reviewed papers
1) B. Pyne, P.R. Akbar, V. Ravindra, H. Saito, J. Hirokawa, T. Fukami, "Slot-Array Antenna Feeder
Network for Space-borne X-band Synthetic Aperture Radar", submitted to the Proceedings of IEEE
Transactions on Antennas and Propagation, under review as of March 12, 2018.
 Presentations
1) B. Pyne, V. Ravindra, P.R. Akbar, H. Saito, J. Hirokawa, "Performance Analysis of Edge-feed
Rectangular Parallel Plate Slot-array Antenna Panel for Compact Space-borne X-band SAR System",
Proceedings of the International Conference on Electromagnetics in Advanced Applications(ICEAA) - IEEE Topical Conference on Antennas and Propagation in Wireless Communications(APWC), Verona, September 2017, pp. 407-410.
 URLs for the Research Results on the Web1) http://www.isas.jaxa.jp/topics/001134.html

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Intel MKL

Number of Processes

2 - 80Elapsed Time per Case

12.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.46
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

153.800.00

SORA-PP

443,619.62

5.55

SORA-LM

92,167.94

47.46

SORA-TPP

175.000.02

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

991.82

0.69

/data

22,842.42

0.42

/ltmp

11,718.76

0.88

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

16.11

0.69

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Rotor/Wing Interaction Simulations
Report Number：R17ECMP10
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4431/
Responsible Representative
Yasutada Tanabe,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Yasutada Tanabe tan@chofu.jaxa.jp

Members
Yasutada Tanabe, Hideaki Sugawara, Masahiko Sugiura, Ryousuke Satou

Abstract
Aerodynamic interaction between a rotor and a fixed wing on a compound helicopter is numericallysimulated to clarify the increase of the arodynamic drag caused by the interaction during high speed
flight.

Reasons for using of JSS2
There is a large number of test cases and an aboundance of computing sources are required.

Achievements of the YearAs the first step, the performance of the isolated rotor and the aerodynamic characteristics of the wingmodels have been clarified.

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

200.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.05
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

150,265.58

0.02

SORA-PP

41,331.21

0.52

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

617.11

0.43

/data

16,682.95

0.31

/ltmp

2,766.93

0.21

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Research of Advanced Rotorcraft
Report Number：R17ECMP11
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4432/
Responsible Representative
Yasutada Tanabe,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Masahiko Sugiura sugiura.masahiko@jaxa.jp

Members
Yasutada Tanabe, Masahiko Sugiura, Hideaki Sugawara

Abstract
Research on advanced technologies of aircraft (helicopter) is conducted to construct and validate an
optimization design tool.
http://www.aero.jaxa.jp/eng/research/frontier/rotary/

Reasons for using of JSS2
It is absolutely necessary to utilize a super computer, regarding understanding aerodynamic
performances which require large scale computations.

Achievements of the Year
Aerodynamically optimal design of helicopter rotor blade.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Computational grids of a hovering helicopter rotor
Publications

JAXA Supercomputer System Annual Report April 2017-March 2018

 Peer-reviewed papers
1) Atthaphon Ariyarit, Masahiko Sugiura, Yasutada Tanabe, and Masahiro Kanazaki, "Hybrid
surrogate-model-based multi-fidelity efficient global optimization applied to helicopter blade
design", Engineering Optimization, September, 2017.

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

12.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.06
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

176,463.66

0.02

SORA-PP

40,651.28

0.51

SORA-LM

3,184.92

1.64

SORA-TPP

4,780.06

0.53

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

140.27

0.10

/data

6,917.32

0.13

/ltmp

813.800.06

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

CFD Analysis of a Multiple Rotor UAV near Walls
Report Number：R17ECMP17
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4433/
Responsible Representative
Yasutada Tanabe,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Yasutada Tanabe tanabe.yasutada@jaxa.jp

Members
Yasutada Tanabe, Hideaki Sugawara

Abstract
Represented by the multiple rotor type UAV (Unmanned Aerial Vehicle), or so-called drone, the flying
robot has been applied to disaster relief and other operations. However, the wind and gust resistence of
this type of drone need to be further improved. Especially in the observation and survey of existing
infrastructures, buidings and bridges, the drones are often required to fly near walls. The flowfields
around the drones are significantly changed with walls nearby and highly depend on the distance between
the drone and the walls. It is considered very effective to incorporate the wall influence on the flight
performance into the flying control rules.
This research is carried out as a part of the Tough Robotics Challenge funded by the ImPACT Programof Council for Science, Technology and Innovation (Cabinet Office, Government of Japan). The
influence of an upper wall and a side wall on the aerodynamics of the multiple rotors is investigatedthrough CFD simulations. Also the flight performance of a drone inside narrow tunnels is under studies.
https://www.jst.go.jp/impact/en/program/07.html

Reasons for using of JSS2
Numerical simulations of multiple rotors are carried out using a CFD code, rFlow3D, developed at
JAXA. The rotor blades are modeled with high fidelity. A large amount of flight conditions must be
considered and each takes a long time of CPU hours. JSS2 supercomputer is a prerequisite of this kindof research.

JAXA Supercomputer System Annual Report April 2017-March 2018

Achievements of the YearA hexa-rotor drone hovering near an upper wall (ceiling) and a side wall is numerically simulated. Whenthe distance between the drone and the wall because shorter than 1.5 times of the rotor diameter, theaerodynamic forces generated by the rotors changes remarkably. The flight performance of a drone
flying inside narrow tunnels is also investigated.

Fig.1 Changes of the flowfields around a hexa-rotor drone due to distance changes
between the drone and a side wall

Publications
 Non peer-reviewed papers
1) Koichi Yonezawa, Hironori Matsumoto, Kazuyasu Sugiyama, Hiroshi Tokutake, Yasutada Tanabe,
Shigeru

Sunada,"DevelopmentofHigh-Performance

Multi-Rotor

Drone",

FourteenthInternational Conference on Flow Dynamics, November 1-3, 2017, Sendai International Center.
2) Yasutada Tanabe, Masahiko Sugiura, Takashi Aoyama, Hideaki Sugawara, Shigeru Sunada, Koichi
Yonezawa, Hiroshi Tokutake, "Influences of Upper and Side Walls on the Performance of a Multiple
Rotor Drone", 6th Asian-Australian Rotorcraft Forum & Heli Japan 2017, November 7-9, 2017,
Kanazawa, Japan.
3) Koichi Yonezawa, Hironori Matsumoto, Kazuyasu Sugiyama, Hiroshi Tokutake, Yasutada Tanabe,
Shigeru Sunada, "Development of a Ducted Rotor for Multicopters", 6th Asian-Australian
Rotorcraft Forum & Heli Japan 2017, November 7-9, 2017, Kanazawa, Japan.
4) Raijo Torita, Takuji Kishi, Hiroshi Tokutake, Shigeru Sunada, Yasutada Tanabe, Koichi Yonezawa,"Modeling of Aerodynamic Characteristics of Drone and Improvement of Gust Response", 6th
Asian-Australian Rotorcraft Forum & Heli Japan 2017, November 7-9, 2017, Kanazawa, Japan.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

720.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.22
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

570,860.89

0.08

SORA-PP

232,987.32

2.92

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

060.80

0.04

/data

3,662.11

0.07

/ltmp

488.280.04

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

Modal decomposition analysis of a flow field around a re-entry capsule
Report Number：R17ECMP20
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4434/
Responsible Representative
Takashi Takahashi, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Yuya Ohmichi ohmichi.yuya@jaxa.jp

Members
Yuya Ohmichi, Kenji Kobayashi

Abstract
Knowledge extraction techniques for large data sets are important because, recently, the computersand numerical simulation techniques have been highly developed and they produced massive datasets .
In this study, we are developing knowledge extraction tools which extract patterns from a large dataobtained by unsteady fluid simulations.

Reasons for using of JSS2
Large amount of memory is necessary for performing the developed knowledge extraction tools.

Achievements of the YearA numerical tool to conducte dynamic mode decomposition and compressed sensing techniques wasdeveloped. The tool was applied to a flow field around a re-entry capsule and we found a novel fluid
phenomenon that had very long time scale.

Publications
 Peer-reviewed papers
1) Y. Ohmichi, Preconditioned dynamic mode decomposition and mode selection algorithms for large
datasets using incremental proper orthogonal decomposition, AIP Advances, 7(7), 075318, 2017.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

72.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.04
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

24,711.62

0.00

SORA-PP

129.300.00

SORA-LM

1,051.62

0.54

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

397.36

0.28

/data

48,990.91

0.91

/ltmp

1,627.60

0.12

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

15.20

0.65

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year

JAXA Supercomputer System Annual Report April 2017-March 2018

SIP CFRP high fidelity modeling technology
Report Number：R17ECMP99
Subject Category：Competitive Funding
URL：https://www.jss.jaxa.jp/ar/e2017/4435/
Responsible Representative
Yutaka Iwahori, Aeronautical Directorate, Structure and Advanced Composite Technology Reasearch
Unit

Contact Information
Akinori Yoshimura yoshimura.akinori@jaxa.jp

Members
Akinori Yoshimura

Abstract
JAXA contributes to the SIP (Cross-ministerial Strategic Innovation Promotion) program, which isgoverned by Cabinet Office, Government of Japan. JAXA takes charge high fidelity modeling of thepolymer matrix composites for aircraft structure. The calculation for the modeling is performed in this
topic.
http://www.jst.go.jp/sip/dl/k03/jst_pamphlet_english.pdf

Reasons for using of JSS2
Damage simulation of the open hole tensile (OHT) test against CFRP was performed using explicit
finite element damage simulation. Huge number of DOFs was necessary for detailed damage simulationin CFRP. Application of the supercomputer system makes such high-computational-cost calculation
possible.

Achievements of the Year
Damage simulation of CFRP under open-hole tensile (OHT) test was performed using ECDM
(Enhanced Continuum Damage Mechanics) model, which was damage model developed in JAXA.
Simulation was performed using ABAQUS/Explicit 2016 on JSS2 system. Each ply of the CFRP
laminate was modeled by one continuum shell element in the thickness direction. ECDM model was
implemented using user-subroutine of ABAQUS. In FY29, ECDM model was modified and final failure
criteria was modified. These modification improved the precision of the simulation results.
Figure 1 shows model overview, and Figure 2 shows the predicted damage.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Model overview of the Open-hole-tension simulation

Fig.2 Predicted damage

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

12 - 120

Elapsed Time per Case

60.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.00
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

3,968.24

0.05

SORA-LM

0.00

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

003.18

0.00

/data

031.79

0.00

/ltmp

651.040.05

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.00

0.00

*1 Fraction of Usage in Total Resources: Weighted average of three resource types (computing, file system,
and archiver)*2 Fraction of Usage: Percentage of usage relative to each resource used in one year