JAXA Supercomputer System Annual Report April 2017-March 2018

Environment Conscious Aircraft Systems Research in Eco-wing Technology:Aerodynamic
System Design Technology
Report Number：R17EA0601
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4358/
Responsible Representative
Yoshikazu Makino,
Aeronautical Technology Directorate Next Generation Aeronautical Innovation Hub Center

Contact Information
Dongyoun Kwak kwak.dongyoun@jaxa.jp

Members
Yoshihisa Aoki, Mitsuhiro Murayama, Dongyoun Kwak, Naoko Tokugawa, Takashi Atobe,
Tatsunori Yuhara, Fumitake Kuroda, Yoshine Ueda, Keisuke Ohira, Hikaru Aono,
Kisa Matsushima, Satoshi Kondo, Tohru Hirai, Kentaro Tanaka, Takashi Matsuno,
Sasamori Monami, Shinsuke Nishimura, Minoru Yoshimoto, Kazuhiro Kubota

Abstract
Innovative drag reduction technologies are investigated to reduce the fuel consumption for aconventional aircraft configuration. Aircraft noise prediction technologies and the conceptual design
technologies are also developed for future aircraft which achieve low noise and high efficiency.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing/

Reasons for using of JSS2
CFD analysis are used for the understanding of aerodynamic characteristics and evaluation of theperformance in the aircraft design phase. Huge calculation resources and costs were required for thehigh fidelity and quick response CFD analysis for the optimum aerodynamic design process on complex
aircraft geometry. JSS2 can achieve those requirements, the cost and time are drastically saved on the
CFD analysis.

Achievements of the Year
Aerodynamic design of the TRA2022 (JAXA Technology reference Aircraft) was performed to reducethe drag on the cruise flight using CFD analysis(Fig.1).
The second configuration of the TRA2022 were designed by applying several drag reduction concepts

JAXA Supercomputer System Annual Report April 2017-March 2018

and know-hows(Fig.2). At first, a low drag airfoil which can reduce not only the friction drag but also
the pressure drag was derived from the NLF design process. The low drag airfoil was chosen on the
TRA2022, and the twist angle of the main wing was optimized to reduce induced drag by controlling thelift distribution. The shock induced separation on the pylon was restricted by modify the wing lower
surface and the pylon geometries. Also, shock characteristics on the upper surface caused by the wing
body interaction were improved. Comparing with the TRA2012A, 10% of the drag reduction wereobtained on the 2nd configuration of TRA2022.

Fig.1 Configurations of the TRA2012A and TRA2022 2nd.

Fig.2 Aerodynamic design of the TRA2022 2nd configuration

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

15 - 300

Elapsed Time per Case

5.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.96
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

7,366,417.13

0.97

SORA-PP

79,733.34

1.00

SORA-LM

46.53

0.02

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

803.85

0.56

/data

48,805.53

0.90

/ltmp

19,594.81

1.48

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

9.15

0.39

*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

Environment Conscious Aircraft Systems Research in Eco-wing Technology:AirframeEngine Noise Reduction Technology
Report Number：R17EA0602
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4359/
Responsible Representative
Yoshikazu Makino,
Aeronautical Technology Directorate Next Generation Aeronautical Innovation Hub Center

Contact Information
Dongyoun Kwak kwak.dongyoun@jaxa.jp

Members
Takehisa Takaishi, Mitsuhiro Murayama, Yasushi Ito, Ryotaro Sakai, Tohru Hirai,
Kentaro Tanaka, Kazuhisa Amemiya, Gen Nakano, Tomoaki Ikeda, Fumitake Kuroda,
Keisuke Ohira, Dongyoun Kwak, Yosuke Matsumura, Seiichiro Morizawa, Ryutaro Furuya

Abstract
Innovative drag reduction technologies are investigated to reduce the fuel consumption for aconventional aircraft configuration. Aircraft noise prediction technologies and the conceptual design
technologies are also developed for future aircraft which achieve low noise and high efficiency.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing/

Reasons for using of JSS2
The JSS2 is used to develop the airframe, engine, and interference noise prediction tools that have highor middle fidelities for applicable to MDO design with high fidelity CFD and FEM analysis. The
airframe-engine installation and/or shielding effects are one of important key issues for the future
aircraft. The accuracy of current low fidelity analysis for the airframe, engine, and interference noise
prediction is not good enough for application to MDO design with high fidelity CFD and FEM analysis
toward the future low-noise aircrafts. The JSS2 is required for development of high or middle fidelity
noise prediction tools for competitiveness in technology.

Achievements of the Year
The accuracy and efficiency of airframe noise prediction (CFD/CAA) tools were improved byincreasing the resolution of sound sources on the complex geomeries. And its effect was evaluated by

JAXA Supercomputer System Annual Report April 2017-March 2018

analysis on benchmarking problems proposed in AIAA Workshop on Benchmark Problems for Airframe
Noise Computations (BANC).
The performance of a JAXA's CFD/CAA solver, UPACS was improved for JSS2 by installing an
improved treatment between each grid block developed in 2016 and a low-dissipation scheme to achieve
higher fidelity and speed-up on the complex geometries . Fig.1,2 show the flow features by CFD and
CAA analisys on a tandem cylinder and a leading edge slat which are the benchmarking problems. Small
scaled vorties were clearly observed on the shear layer region and separation area. The resolution forsound sources was increased by combination of improved higher-order scheme using a low-dissipation
upwind SLAU scheme and a central difference scheme developed in 2017. Furthermore, the convergenceof the numerical analysis was also enhanced as well as higher flow resolutions. Improvement of theaccuracy and efficiency on on the complex geometries were achieved on JAXA's CFD/CAA tools.

Fig.1 Simplified benchmark problem for landing-gear noise predictionJAXA Supercomputer System Annual Report April 2017-March 2018

Fig.2 Benchmark problem for slat noise prediction(JAXA/NASA Collaboration Research: 30P30N wind tunnel test)

Publications
 Non peer-reviewed papers
1) Tomoaki Ikeda, et.al., "Aerodynamic Noise Simulations Resolved by Higher-order Spatial Schemes
on JAXA's UPACS", 14th International Conference on Flow Dynamics, 2017.11.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

20 - 800

Elapsed Time per Case

349.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.30
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

10,627,256.06

1.41

SORA-PP

2,057.55

0.03

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

497.16

0.34

/data

20,313.45

0.38

/ltmp

9,073.39

0.68

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

95.39

4.10

*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

FINE (Flight Investigation of skiN-friction reducing Eco-coating)
Report Number：R17EA0603
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4360/
Responsible Representative
Yoshikazu Makino, Aeronautical Technology Directorate, Aviation Systems Research Unit

Contact Information
Mitsuru Kurita kurita@chofu.jaxa.jp

Members
Fumitake Kuroda, Mitsuru Kurita

Abstract
This study develops a more effective riblet pattern

to reduce the skin friction in the turbulent

boundary layer by using DNS. The optimized riblet pattern by the DNS is painted on a experiment
airplane, the effects of the reducing skin friction is evaluated in flight.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing

Reasons for using of JSS2
CFD (DNS) analysis are used for developing a optimized riblet pattern that is effective to reduce theskin friction in turbulent boundary layer.Huge calculation resources and costs are required for the highfidelity and quick response CFD analysis for obtaining the optimum riblet pattern. Use of JSS2 isindispensable for these requirements; the cost and time on the CFD analysis are drastically saved .

Achievements of the Year
We have performed a series of direct numerical simulations of a turbulent channel flow over riblets inorder to understand the basic characteristics regarding the riblets for the flight testing in the 'FINE'
project. Consequently, the performance of the riblets, i.e. a depednence of S^+ (a riblet spacing
normalzied by wall units) on the drag reduction, have been successfully clarified.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Vortical structures and wall shear stress in the DNS. Isosurfaces refer topositive values of the second invariant of the fluctuating velocity tensor,
whereas the color contours show the wall shear-stress distribution.

Publications
 Non peer-reviewed papers
1) Kurita, M., Nishizawa, A., Kwak, D., Iijima, H., Iijima, Y., Takahashi, H., Sasamori, M., Abe, H.,
Koga, S., Nakakita, K., Kuroda, F., "FINE: Flight Investigation of skiN-friction reducing Eco-coating,First Flight Test", 55th Aircraft Symposium, 2017.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelizatio

Number of Processes

64 - 512

Elapsed Time per Case

500.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.37
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

11,499,337.06

1.53

SORA-PP

84.29

0.00

SORA-LM

14.69

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

006.34

0.00

/data

9,858.96

0.18

/ltmp

878.91

0.07

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.99

0.04

*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

Environment Conscious Aircraft Systems Research in Eco-wing Technology: Contract
Research on Fan-Noise Simulation
Report Number：R17EA0620
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4361/
Responsible Representative
Yoshikazu Makino, Aeronautical Technology Directorate Next Generation Aeronautical Innovation
Hub Center

Contact Information
Mitsuhiro Murayama murayama.mitsuhiro@jaxa.jp

Members
Ryotaro Sakai, Shota Hayakawa, Soshi Kawai, Yuma Fukushima, Mitsuhiro Murayama, Yasushi Ito

Abstract
In a research of environment-conscious aircraft systems resarch for environmental conscious aircraft
technology named "Research for Eco-Wing technology", innovative drag reduction technologies areinvestigated to reduce the fuel consumption for a conventional aircraft configuration. Aircraft noise
prediction technologies and the conceptual design technologies are also developed for future aircraft
which achieve low noise and high efficiency. The objective of this contract research on fan-noise
simulation is to improve the stability of the computations using Linearlized Euler Equations (LEE) topredict the fan noise shielding/interference effect by airframe.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing/

Reasons for using of JSS2
The JSS2 is used to develop the airframe, engine, and interference noise prediction tools that have highor middle fidelities for applicable to MDO design with high fidelity CFD and FEM analysis. The
airframe-engine installation and/or shielding effects are one of important key issues for the future
aircraft. The accuracy of current low fidelity analysis for the airframe, engine, and interference noise
prediction is not good enough for application to MDO design with high fidelity CFD and FEM analysis
toward the future low-noise aircrafts. The JSS2 is required for development of high or middle fidelity
noise prediction tools for competitiveness in technology.

JAXA Supercomputer System Annual Report April 2017-March 2018

Achievements of the YearThe source code and compile options of a fan-noise simulation code were modified so that the code
would efficiently work on JSS2 SORA-MA system. The peformance of speed and efficiency inparallelization was evaluated by changing the number of process/thread to estimate computational
resources required for practical predictions on fan noise shielding/interference effect by airframe.
Publications
N/A

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

32 - 1024

Elapsed Time per Case

10.00 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

154,868.66

0.02

SORA-PP

0.00

0.00

SORA-LM

0.07

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

192.71

0.13

/data

54,481.85

1.01

/ltmp

3,327.95

0.25

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

5.41

0.23

*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

Environment Conscious Aircraft Systems Research in Eco-wing Technology: Contract
Work on CFD Code Modifications
Report Number：R17EA0621
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4362/
Responsible Representative
Yoshikazu Makino, Aeronautical Technology Directorate Next Generation Aeronautical Innovation
Hub Center

Contact Information
Mitsuhiro Murayama murayama.mitsuhiro@jaxa.jp

Members
Yosuke Matsumura, Masayuki Kakehi, Mitsuhiro Murayama, Tomoaki Ikeda, Yasushi Ito

Abstract
In a research of environment-conscious aircraft systems resarch for environmental conscious aircraft
technology named "Research for Eco-Wing technology", innovative drag reduction technologies areinvestigated to reduce the fuel consumption for a conventional aircraft configuration. Aircraft noise
prediction technologies and the conceptual design technologies are also developed for future aircraft
which achieve low noise and high efficiency.
As part of research, an overset grid method with higher order interpolation is introduced into a CFD
code to reduce time-consuming work for grid generation around complicated aircraft configurations,while achieving high resolution of noise sources with higher-oder numerical scheme. In this contract
work, operation check and debug of the modified CFD code on JSS2 is conducted.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing/

Reasons for using of JSS2
The JSS2 is used to develop the airframe, engine, and interference noise prediction tools that have highor middle fidelities for applicable to MDO design with high fidelity CFD and FEM analysis. The
airframe-engine installation and/or shielding effects are one of important key issues for the future
aircraft. The accuracy of current low fidelity analysis for the airframe, engine, and interference noise
prediction is not good enough for application to MDO design with high fidelity CFD and FEM analysis
toward the future low-noise aircrafts. The JSS2 is required for development of high or middle fidelity
noise prediction tools for competitiveness in technology.

JAXA Supercomputer System Annual Report April 2017-March 2018

Achievements of the Year
The pre-processing in the modified code was developed with debuggin through application to a large
scale practical problem on JSS2 SORA-PP system.

Publications
N/A

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

300

Elapsed Time per Case

12.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.09
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

551.900.00

SORA-PP

84,869.11

1.06

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

024.38

0.02

/data

50,579.73

0.94

/ltmp

1,429.07

0.11

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.01

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

Environment Conscious Aircraft Systems Research in Eco-wing Technology: Collaborative
Research on Future Aircraft Conceptural Design
Report Number：R17EA0622
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4363/
Responsible Representative
Yoshikazu Makino, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation
Hub Center

Contact Information
Seiichiro Morizawa morizawa@mech.tottori-u.ac.jp

Members
Seiichiro Morizawa

Abstract
The discussion on the planforms of forward-swept wings for the furture aircraft design was conductedwith CFD. For this purpose, a parametric study of the planforms was conducted, and the influecnes ofthe design parameters on the aerodynamic characteristics and the flow fields are investigated.
http://www.aero.jaxa.jp/eng/research/ecat/ecowing/

Reasons for using of JSS2
In order to conduct the parametric study with CFD, a huge computational cost is required. It is almost
impossible to have a computation by the workstation at our laboratory. So the computations with a supercomputer are necessary to conduct our research because the available memory and CPU ofsupercomputer like JSS2 are much larger than the workstation at our laboratory.

Achievements of the Year
The planforms of the leading and trailing reversed wing of Boeing767 was employed as the baseforward-swept wing. The aerodynamic characteristics and flow fields of the base wing were investigated.
It is confirmed that the lift and drag slopes change at the angle of attack of 4deg. This result shows thatthe flow separation from the outer wing side to the inner wing side has occurred near the trailing edge.
Next, the parameters of the planform are defined as shown in Fig. 2, and the aerodynamic performanceof these planforms were investigated. As the result, the semispan length has better performance on the
aerodynamic characteristcs when the length becomes larger. However, the changes in inner/outer swept-

JAXA Supercomputer System Annual Report April 2017-March 2018

forward angles and chord length at the kink position of the wing contribute less to the change in the
aerodynamic characteristcs. Then, the aerodynamic characteristcs becomes worse when the extremechange in outer angle and the chord length is observed.

Fig.1 Computational results of baseline forward-swept wing

Fig.2 Parameter definition of forward-swept wing planform

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
N/A

Usage of JSS2
 Computational Information
Parallelization Methods

N/A

Thread Parallelization Methods

OpenMP

Number of Processes

1

Elapsed Time per Case

660.00 minutes

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.02
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

197,997.85

0.03

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

162.71

0.11

/data

3,370.26

0.06

/ltmp

790.550.06

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.01

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 on high load compressor technology
Report Number：R17EA0711
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4364/
Responsible Representative
Toshiya Nakamura, Next Generation Aeronautical Innovation Hub Center

Contact Information
Junichi Kazawa kazawa.junichi@jaxa.jp

Members
Junichi Kazawa, Yuntae Lee, Takafumi Kanayama

Abstract
For the international joint development of jet engines, it aims to develop and demonstrate core engine
technology with little experience in Japan. In order to achieve high aerodynamic performance of acompact size and a total pressure ratio of 20 or more, we designed a multi-stage axial compressor with
mixed flow compressor applied in the final stage and confirmed its validity by numerical analyses.
http://www.aero.jaxa.jp/eng/research/ecat/greenengine/

Reasons for using of JSS2
In multistage compressor analyses, the number of grid points is large. It is necessary to analyze manycases to obtain a performance curve. It is necessary to use supercomputers in order to produce results ina limited time period and feed back to the multistage compressor design.

Achievements of the Year
The aerodynamic performance was predicted by multi-stage steady-state analysis for the high pressurecompressor with seven stage axial compressor and one mixed flow compressor designed by JAXA.
Although there was a problem with aerodynamic performance in the initial design shape, we confirmedthat it was improved by the improved design and confirmed the validity of the high pressure comressor
design.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 High Pressure Compressor (Designed by JAXA)

Fig.2 Improved design result (total pressure distribution)

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

66 - 95

Elapsed Time per Case

5.50 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.21
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

1,482,092.70

0.19

SORA-PP

48,319.33

0.60

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

019.75

0.01

/data

197.55

0.00

/ltmp

4,045.76

0.31

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 of internal flow of aircraft combustor for Green Engine Project.
Report Number：R17EA0714
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4365/
Responsible Representative
Toshiya Nakamura,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Mitsumasa Makida makida.mitsumasa@jaxa.jp

Members
Mitsumasa Makida(JAXA), Naoki Nakamura(ASIRI)

Abstract
In the development process of aircraft combustors, air mass flow distribution between fuel nozzles,
dilution and cooling air holes on the liner effects performances of combustors. So it is important tounderstand the internal flow and estimate the mass flow distribution. In this research, we conduct coldflow simulations of internal flow inside the combustor which faithfully simulates the configuration ofpractical combustor. Then we aim to develop methods to analyze aerodynamic performance of
combustors such as air mass flow distribution with high accuracy.
http://www.aero.jaxa.jp/eng/research/ecat/greenengine/

Reasons for using of JSS2
It is important to do parametric case study with slightly different geometry, and each case needs large
scale simulation. To conduct such simulation effectively, we need the super computer with highparallelization efficiency.

Achievements of the YearIn this fiscal year, we conducted cold-flow simulations for a single-sector combustor. These simulations
aimed to estimate the effect of the angle of conical heat shield on the internal flow of the combustor.
Fig.1 shows the calculation girds and boundary conditions and Fig.2 shows stream lines from the pilot
fuel nozzle for the heat shield angle of 45 degree. The calculation region starts from the inlet of thepressure-resistant casing to the outlet of the combustor. Calculations were also conducted for the angleof 50, 55 and 60 degree cases. To do parametric studies by changing minimum parts of combustor

JAXA Supercomputer System Annual Report April 2017-March 2018configuration, the overset boundary method, in which corresponding parts can be changed, is effective.

Fig.1 Calculation grids and boundary conditions for single-sector combustor

Fig.2 Stream lines from pilot fuel nozzle

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Presentations
1) Seiji YOSHIDA, Takeshi YAMAMOTO, Mitsumasa MAKIDA, Kazuo SHIMODAIRA(JAXA) andNaoki NAKAMURA(ASIRI), "Effects of Flare Angle of Conical Heat Shield on Combustion
Characteristics of Lean Axially Staged Combustor", 45th Annual Conference of GTSJ, 2017.10.

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelizatio

Number of Processes

64

Elapsed Time per Case

250.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.13
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

1,024,849.05

0.14

SORA-PP

1,944.38

0.02

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

093.25

0.06

/data

2,189.21

0.04

/ltmp

1,193.58

0.09

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.14

0.01

*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

Noise suppression technology for aircraft jet engines
Report Number：R17EA0716
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4366/
Responsible Representative
Toshiya Nakamura
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Shunji ENOMOTO enomoto.shunji@jaxa.jp

Members
Shunji ENOMOTO, Tatsuya ISHII, Kae ITO, Nobuhiko YAMASAKI

Abstract
Noise generated from the jet engine is dominant to total aircraft noise level and it is very important to
reduce this. In this project, demonstration of exhaust noise reduction by changing exhaust duct shape,and study of noise reduction technique by numerical analysis are carried out.
http://www.aero.jaxa.jp/eng/research/ecat/greenengine/

Reasons for using of JSS2
The calculation was LES with a large amount of computation and storage usage. It was necessary to use
SORA-PP and SORA-FS.

Achievements of the Year
In order to investigate the behavior when sound waves pass through a jet, LES calculation of a jet was
performed using UPACS-LES, and sound waves were injected from the side of the jet. The temperature
distribution is shown in Fig. 1. Jet's Mach number is 0.8. Figure 2 shows the sound pressure. It turned
out that the sound reflected, refracted, and diffused by the jet. Also 3-D flow field around the apertureof the acoustic liner was simulated to study the mechanism of the improvement of sound absorbing
performance when the bias flow presents for the aperture. Figure 3 shows the vorticity contour near thetapered aperture and we can observe that the distribution of the turbulent vortices, which is considered
to be the dissipation source, is wider in space in the bias flow case.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Temperature

Fig.2 Sound pressure

Fig.3 Vorticity contour near the aperture, without(left) and with(right) the bias flow.

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
N/A

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

12 - 36

Elapsed Time per Case

39.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.18
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.45

0.00

SORA-PP252,793.70

3.17

SORA-LM

0.00

0.00

SORA-TPP

8,282.24

0.92

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

022.12

0.02

/data

2,213.67

0.04

/ltmp

2,678.57

0.20

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

11.28

0.49

*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

Study of Green engine (study of ultrahigh-temperature low NOx emission combustor
technology) atomization process of a fuel spray nozzle in a practical geometry
Report Number：R17EA0730
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4367/
Responsible Representative
Toshiya Nakamura,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Kazuaki Matsuura matsuura.kazuaki@jaxa.jp

Members
Kazuaki Matsuura, Mitsumasa Makida, Naoki Nakamura, Jun Iino, Huilai Zhang

Abstract
The atomization process occurs in the narrow region which is vicinity of the injection outlet in apractical geometry fuel injector under development in Green engine project. Therefore, it is difficult tounderstand the atomization phenomena only by experiment.

The objective of this work is tounderstand the atomization mechanism by numerical study which calculated the atomization field in thenear region of the injection outlet.

Reasons for using of JSS2
The particle diameter is order of 10 micron in the experiment. In order to calculate this size ofatomization field precisely,
large scale calculation with more than a few of hundred million of cells which size is a few micron meterorder is needed andthe use of super computer is necessary.

Achievements of the Year
Numerical analysis with VOF method of the fuel atomization field is conducted and revealed thecondition of the particles broken up from different speed of cross-flow jets.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Atomization process of fuel spray nozzle in a practical geometry. Side view
(Green:High speed cross flow jet, Yellow:Low speed cross flow jet)Fig.2 Atomization process of fuel spray nozzle in a practical geometry. Upper view
(Green:High speed cross flow jet, Yellow:Low speed cross flow jet)

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
N/A

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

768

Elapsed Time per Case

140.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.60
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

13,261,007.18

1.76

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

120.43

0.08

/data

32,610.17

0.60

/ltmp

5,099.83

0.38

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.14

0.01

*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

Aerodynamic Characteristics Improvement of Quad Tilt Wing VTOL Plane
Report Number：R17EA0901
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4368/
Responsible Representative
Shigeru Hamamoto, Aeronautical Technology Directorete, Aerodyamics Research Unit

Contact Information
Yoshihisa Aoki aoki@chofu.jaxa.jp

Members
Yoshihisa Aoki

Abstract
Improvement of aerodynamic characteristics of Quad Tilt Wing VTOL Plane in cruise.

Reasons for using of JSS2
It takes a lot of time to calculate using workstation.

Achievements of the Year
Wing aspect ratio sensitivity analysis ofusing FaSTAR.

Publications
N/A

practical demonstration unmanned plane was conducted

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

160 - 640

Elapsed Time per Case

10.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.01
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

23,331.00

0.00

SORA-PP

3,136.13

0.04

SORA-LM

3.67

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

035.76

0.02

/data

596.05

0.01

/ltmp

244.14

0.02

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

Prediction of aerothermal environment around atmospheric entry vehicles withsophisticated numerical tools
Report Number：R17EA1402
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4369/
Responsible Representative
Shigeru Hamamoto, Aeronautical Technology Directorate, Aerodynamics Research Unit

Contact Information
Takashi Ozawa ozawa.takashi@jaxa.jp

Members
Adrien Lemal, Toshiyuki Suzuki, Takashi Ozawa, Toru Yamada, Yuuto Higuchi, Ryotaro Murakami

Abstract
In this study, we try to enhance physical models for high temperature gas and numerical simulation
method to accurately predict heating and aerodynamic characteristics at hypersonic atmospheric entry.
We aim to develop high fidelity simulation tool by demonstrating improvement of prediction accuracy
by comparing experimental data and simulation results with the newly proposed model and method.

Reasons for using of JSS2
In order to evaluate uncertainties in nonequilibrium thermochemical models and freestream conditions,supercomputer was used to perform a large number of CFD runs by changing physical models and flow
conditions.

Achievements of the Year
In order to predict test flow conditions generated by expansion tube, measured shock velocity, staticpressure and pitot pressure were compared with calculated results. As a result of comparison, It was
found that shock velocity comparison shows agreement within 10%. Static pressure comparison showedreasonable agreement. Pitot pressure comparison showed overestimation by calculation. On the view
point of overestimation of pitot pressure, possibility of 10 times higher forward rate constant of CO2
dissociation reaction with short holding time is highlighted. With respect to contact surface rise delay,
direct simulation of pitot tube with sensor cover was conducted. As a result of simulation, possibility that
sensor cover causes surface rise delay was presented. In our future work, in order to validate this

JAXA Supercomputer System Annual Report April 2017-March 2018

simulated result, test flow temperature and CO2 number density will be measured by absorption methodwith a use of continuous light source.

Fig.1 Counter plot of pressure around pitot tube(t=0.04ms(left), 0.1ms(right))

Fig.2 Effect of sensor cover on measured pressure

Publications

JAXA Supercomputer System Annual Report April 2017-March 2018

 Presentations
1) Yamada, T., Lemal, A., Matsuyama, S., Nomura, S., Takayanagi, H., Fujita, K., Matsui, M.,"Numerical Analysis of Flowfield around Pitot Tube in an Expansion Tube," 35th Aerospace
Numerical Simulation Symposium, National Olympic Memorial Youth Center(Sibuya, Tokyo), Jul.
29-30, 2017.
2) Yamada, T., Higuchi, Y., Lemal, A., Matsuyama, S., Nomura, S., Takayanagi, H., Fujita, K., Matsui,M., "Determination of Test Flow Conditions Simulating Mars Entry Environment in an Expansion
Tube," 61th Symposium on Space Sciences and Technology, Toki-messe (Niigata, Niigata), Oct.
25-27, 2017.
3) Yamada, T., Higuchi, Y., Lemal, A., Matsuyama, S., Nomura, S., Takayanagi, H., Fujita, K., Matsui,M., "Prediction of thermochemical conditions of CO2 Expansion Tube Flow," H29 Symposium on
Flight Mechanics and Astrodynamics, ISAS (Sagamihara, Kanagawa), Dec. 7-8, 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

16 - 52

Elapsed Time per Case

20.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.07
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

478,847.82

0.06

SORA-PP

5,479.16

0.07

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

514.98

0.36

/data

10,147.10

0.19

/ltmp

9,765.63

0.74

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

Reinforcing of RCS Control Ability by Utilizing Jet Interaction Force
Report Number：R17EA1403
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4370/
Responsible Representative
Shigeru Hamamoto, Aeronautical Technology Directorate, Aerodynamics Resuearch Unit

Contact Information
Hajime Miki miki.hajime@jaxa.jp

Members
Hajime Miki, Yoshiki Takama, Keisuke Fujii

Abstract
A capsule lacks its attitude control ability during a reentry flight. The purpose of this study is to utilize
RCS interaction force for reinforcing the ability by changing the external shape locally.

Reasons for using of JSS2
The use of JSS2 was nessesary for conducting CFD analysis to survey the validity of the capsule shapechange in a short period before manifucturing a wind tunnel model.

Achievements of the Year
HRV capsule was changed its external shape near the RCS, and CFD analysises using FaSTAR code
were performed on that capsule to examine variations of the interaction force. Figure 1 shows pressure
distributions on its after-body, and it seems the RCS interaction causes mainly on the shape changed
part. As shown in Fig. 2, the interaction force increased in a direction of reinforcing the RCS control
ability. The design and manufacuture of wind tunnel model was carried out based on this CFD result.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Pressure distribution around RCS

Fig.2 Variation of RCS interection force

Publications
 Presentations
1) Miki, H., Fujii. K. "Prediction of Jet Interaction Heating on a Reentry Capsule", SciTech2018,
AIAA-2018-0382.

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

128

Elapsed Time per Case

20.00 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

417,613.89

0.06

SORA-PP139.200.00

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

013.70

0.01

/data

1,229.21

0.02

/ltmp

2,669.27

0.20

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

Active Fluid Flow Control using DBD Plasma Actuators
Report Number：R17EA1477
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4371/
Responsible Representative
Shigeru Hamamoto, Aeronautical Technology Directorate, Aerodymics Research Unit

Contact Information
Yoshihisa Aoki aoki@chofu.jaxa.jp

Members
Yoshihisa Aoki

Abstract
Improvement of aerodynamic characteristics using DBD plasma actuators.

Reasons for using of JSS2
It takes a lot of times to calculate using workstation.

Achievements of the Year
Unsteady fluid flow analysis around cylinder was conducted using FaSTAR.

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

320

Elapsed Time per Case

200.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.03
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

258,899.81

0.03

SORA-PP

99.39

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

035.76

0.02

/data

596.05

0.01

/ltmp

244.14

0.02

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 on the aircraft structures and advanced composite materials
Report Number：R17EA1601
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4372/
Responsible Representative
Yutaka Iwahori,
Aeronautical Directorate, Structure and Advanced Composite Technology Reasearch Unit

Contact Information
Akinori Yoshimura yoshimura.akinori@jaxa.jp

Members
Akinori Yoshimura, Ryo Higuchi, Masaya Ebina

Abstract
Application of the composite materials will contribute to improving the performance of aircraft andspacecraft components. JAXA conducts researches for overcoming weaknesses of current composite
materials, clarifying unknown aspects such as fracture mechanisms, improving performance and enabling
application to design technology.
http://www.aero.jaxa.jp/eng/research/basic/structure-composite/

Reasons for using of JSS2
We performed damage simulation of CFRP under impact loading in order to assess the design safetyof CFRP structure. For precise simulation, each CFRP lamina must be modeled separately, and huge
number of DoFs are needed. Application of the supercomputer system makes such high-computationalcost calculation possible.

Achievements of the YearLow-velocity impact damage simulation was performed using ECDM (Enhanced Continuum Damage
Mechanics) model, which was damage model developed in JAXA. Low-velocity impact tests were
performed based on the ASTM D7136 standard, and damage was measured by non-destructive
inspection (NDI). In FY29, ECDM model was modified in order to improve the precision. Moereover,simulations were performed for various CFRP prepregs,

various stacking sequences and various

boundary conditions.
Simulation was performed using ABAQUS/Explicit 2016 on JSS2 system. Each ply of the CFRPJAXA Supercomputer System Annual Report April 2017-March 2018

laminate was modeled by one continuum shell element in the thickness direction. ECDM model was
implemented using usersubroutine of ABAQUS.
Figure 1 shows model overview, and Figure 2 compares damage area predicted by simulation andmeasured damage area. Both results agree well, and the validity and precision of the model were
demonstrated.

Fig.1 Model overview of the low-velocity impact simulation

Fig.2 Comparison of the measured and predicted damage area

Publications
 Presentations
1) Akinori Yoshimura, Masaya Ebina, Kenichi Sakaue, Anthony M. Waas, 'High Fidelity Simulation of
Low Velocity Impact Behavior of CFRP Laminate', 32nd American Society for Composites
Technical Conference, Oct. 2017, Purdue University, IN, USA

JAXA Supercomputer System Annual Report April 2017-March 20182) Masaya Ebina, Akinori Yoshimura,

Kenichi Sakaue, Yuichiro Aoki, 'Low Velocity Impact

Simulation of CFRP Laminates Considering Microscopic Damage Interaction', 33rd American
Society for Composites Technical Conference, Sep. 2018, Seattle, WA, USA (scheduled)

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

12 - 120

Elapsed Time per Case

340.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.03
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

35,294.26

0.44

SORA-LM

751.300.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

036.56

0.03

/data

365.58

0.01

/ltmp

7,486.98

0.56

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

Unsteady Aerodynamics Simulation of Frontier Region
Report Number：R17EA1901
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4373/
Responsible Representative
Takashi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Atsushi Hashimoto hashimoto.atsushi@jaxa.jp

Members
Takashi Ishida, Atsushi Hashimoto, Kenji Hayashi, Takashi Aoyama, Takahiro Yamamoto,
Masashi Kanamori

Abstract
The objective of this study is to realize CFD that can be used in the entire flight envelope by
investigating precise CFD technologies that can be applied to unsteady phenomena, such as aerodynamic
buffeting and flow separation.
http://www.aero.jaxa.jp/eng/research/basic/numerical/unsteady-cfd/

Reasons for using of JSS2
Unsteady simulation is more than 1000 times cost compared with steady simulation. We need asupercomputer within a reasonable time.

Achievements of the Year
We computed a transonic buffet on NASA-CRM wing-body configuration. We used the Zonal-DES
method and the wall model for the RANS region. We could reduce the number of grid by one-third. The
Mach number is 0.85, the Reynolds number is 1.5x106, and the attack angle is 4.87deg. The grid was
generated with BOXFUN and the number of grid is 21M cells. The average and RMS of pressure areshown in (Fig.1) and (Fig.2). The results with the wall model is close to the experimet. The instantaneous
surface pressure is shown in (Fig.3). The buffet cells convects in the spanwise direction.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Average of pressure

Fig.2 RMS of pressure

Fig.3 Surface pressure

Publications
 Presentations
1) Atsushi Hashimoto, Takashi Ishida, Takashi Aoyama, Yuya Ohmichi, Takahiro Yamamoto, andKenji Hayashi. "Current Progress in Unsteady Transonic Buffet Simulation with Unstructured Grid
CFD Code", 2018 AIAA Aerospace Sciences Meeting, AIAA SciTech Forum, (AIAA 2018-0788)

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

512 - 2024

Elapsed Time per Case

15.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 2.35
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

19,589,093.12

2.60

SORA-PP

41,299.17

0.52

SORA-LM

1,028.15

0.01

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

194.41

0.13

/data

16,592.12

0.31

/ltmp

2,087.98

0.16

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

2.26

0.10

*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

Study on Acoustic Analysis Techniques to Improve Aerospace Interior Acoustic
Environment
Report Number：R17EA1902
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4374/
Responsible Representative
Takashi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Takashi Takahashi takahashi.takashi@jaxa.jp

Members
Takashi Takahashi, Yuya Ohmichi, Masashi Kanamori, Takahiro Higash, Kento Yamada,
Kan Ohkubo, Tatsuya Narumi

Abstract
We study the numerical prediction approaches of sound sources, propagation and transmission forpractical aerospace applications (e.g. aircraft interior noise prediction, etc.). Our aim is to upgrade therespective technologies in order to attain the world’s most advanced high speed and sophistication levels,and to develop an integrative numerical prediction tool that accommodates the seamless application oftechnologies.

Reasons for using of JSS2
In order to accurately reproduce to characteristics of jet noise, a calculation grid need to resolution
enough to capture small fluid phenomena. Therefore, the number of grid points used for acoustic analysis
is very large, and it is necessary to use a computer capable of large scale parallelization to perform
calculations.

Achievements of the YearThe noise generated from subsonic jet was analyzed by CFD. Analysis was performed on two kinds of
nozzle shapes(Fig.1), and frequency characteristics of each noise were evaluated. Flow field analysis used
the unstructure analysis solver FaSTAR. From the analysis results, it was possible to confirm thedifference in vortex structure due to the difference nozzle shape (Fig.2). From the analysis result of thenoise, the frequency distribution close to the experimental value can be reproduced in the low frequency.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Picture of nozzle geometry

Fig.2 Vortex structure of each nozzles

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

2 - 800

Elapsed Time per Case

30.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.38
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

2,834,770.96

0.38

SORA-PP

8,270.53

0.10

SORA-LM

1,955.61

0.01

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

1,603.54

1.11

/data

37,329.55

0.69

/ltmp

9,393.61

0.71

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

9.50

0.41

*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

Study on Simulation Technology to Realize Front Loading of Combustor Design Process
Report Number：R17EA1903
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4375/
Responsible Representative
Yasuhiro Mizobuchi, Aeronautical Technology Directrate, Numerical Simulation Research Unit

Contact Information
Yasuhiro Mizobuchi mizo@chofu.jaxa.jp

Members
Manabu Hisida, Taisuke Nambu, Hiroki Yao, Shogo Yasuda, Yuichi Matsuo,
Yasuhiro Mizobuchi, Hiroyuki Abe, Takeshi Okabe, Shingo Matsuyama

Abstract
Enhancement of front loading of engine design process by simulation technology.

Reasons for using of JSS2World-level research in this field requires massively parallel huge computational resource and only socalled supercomputer system can provide it.

Achievements of the Year
Separation of a turbulent boundary layer is one of the key phenomena in aeronautical applications suchas combustors and airfoils. In the present study, we have performed direct numerical simulation of apressure-induced separation bubble. The Reynolds number based on inlet momentum thickness andfreestream velocity is Re_θ= 1500, which is the largest Reynolds number ever performed in thisconfiguration. Number of grid points used are 13 billion to resolve the essential motions. Figure 1 shows
visualization of vortical structures for Re_θ= 1500, which highlights the clustering of fine vorticalstructures in the separated shear layer (see the enlarged view of Fig. 1).
Robustness of an analysis solver for 2 phase flow was improved, and 4 cases of primary atomization
detailed analysis were finished.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Vortical structures observed in the DNS for Re_θ=1500 (white: positive valuesof the second invariant of fluctuating velocity tensor Q). The upper panel
denotes the perspective view, whereas the lower panel refers to the side view.

Fig.2 Visualization of air-liquid interface.

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Peer-reviewed papers
1) H. Abe, "Reynolds-number dependence of wall-pressure fluctuations in a pressure-induced
turbulent separation bubble," J. Fluid Mech., Vol. 833, pp. 563-598 (2017).
2) H. Abe and R.A. Antonia, "Relationship between the heat transfer law and the scalar dissipation
function in a turbulent channel flow," J. Fluid Mech., Vol. 830, pp. 300-325 (2017).
3) Y.Mizobuchi and T. Takeno, "A numerical study on the detailed structure of hydrogen/air Bunsen
flame," J. Comb. Society of Japan, vol.59, No.190, pp.303-311(2017).
 Presentations
1) H. Abe, Y. Mizobuchi and Y. Matsuo, "DNS study on Reynolds-number dependence of a turbulent
boundary layer with separation and reattachment," Proc. of the 16th European Turbulence
Conference (Stockholm, Sweden, August 21-24, 2017).
2) H. Abe, "DNS and modeling of a turbulent boundary layer with separation and reattachment," The47th LES reserch meeting(Institute of Industrial Science, the University of Tokyo, Sept. 12, 2017).
3) H. Abe,

"Direct numerical simulation of a turbulent boundary layer with separation andreattachment over a wide range of Reynolds numbers," CTR Tea Seminar, Center for Turbulence
Research, Stanford University, USA, November 10, 2017.
4) Y. Mizobuchi, T. Takeno, "Investigation on Tip Opening phenomenon of hydrogen/air Bunsen
flame by use of detailed numerical simulation," 55th Japanese Combustion Symposium, Toyama
International Conference Center, Nov. 13, 2017.
5) H. Abe,

"Direct numerical simulation of a turbulent boundary layer with separation andreattachment at Re_θ=1500," Bulletin of the American Physical Society 70th Annual Meeting of
the APS Division of Fluid Dynamics (Denver, CO, November 19-21, 2017), Vol. 62, No. 14, p. 208.
6) T. Nambu, Y. Mizobuchi, "Numerical Simulation of Liquid Fuel Atomization in a Cross-flow
involved with Wall Impingement," 26th ILASS-Japan Symposium, AIST Tokyo Waterfront, Dec. 20,20177) .H. Abe, "DNS of a turbulent boundary layer with separation and reattachment: Study of effectsof Reynolds number and pressure gradient," Prof. of the 33th TSFD symposium(Institute ofIndustrial Science, the University of Tokyo, March 5, 2018).

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

Both of MPI and XPFortranThread Parallelization Methods

OpenMP

Number of Processes

8 - 384

Elapsed Time per Case

2,000.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 7.60
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA63,631,143.11

8.47

SORA-PP

42,086.56

0.53

SORA-LM

386.11

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

764.37

0.53

/data

32,676.13

0.60

/ltmp

5,214.42

0.39

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

39.10

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

Research on Particle-based Fluid Simulation Method for Improvement of Design andDevelopment in Aeronautics
Report Number：R17EA1907
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4376/
Responsible Representative
Takashi Aoyama, Numerical Simulation Research Unit, Aeronautical Technology Directorate

Contact Information
Kenichi Kubota kubota.kenichi@jaxa.jp

Members
Kenichi Kubota, Takashi Takahashi, Hiroki Tsujimura

Abstract
In this project, a numerical code using particle method, which is known to be a meshless method tosimulate fluid governed by Navier-Stokes equation, is being developed, and we investigate applicabilityof particle methods to aeronautics, especially the improvement in design and development of aircrafts.

Reasons for using of JSS2
We used JSS2 to reduce computation time, because the computational cost of the particle method isknown to be higher than grid methods. Parallel computing is effective on the reduction of computation
time, and massive parallel computation on a super computer is planned in future studies.

Achievements of the YearFor developing a numerical simulation method of water drops exposed to airflow, a model to simulate
aerodynamic force acting on a droplet composed of many particles was developed and implemented tothe developing code. We simulated droplet breakup and compared the results with the breakup patterns
which is known to be classified by the initial Weber. As a result, it was found that the characteristic
behavior such as no-breakup in the low Weber number about 10 and sheet stripping in high Weber
number about 150 can be captured with the developed model, whereas bag and bag-and-stamen breakup
did not appear in the middle Weber number. Therefore, it can be said that the developed dynamic
pressure model is applicable to the droplet exposed in the airflow for the Weber number above 150.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Result of numerical analysis for four Weber numbers (left) and experimentally known
breakup patterns (right).

Publications
 Presentations
1) Hiroki Tsujimura, Kenichi Kubota, Tetsuya Sato, Takashi Takahashi, Keiichi Murakami,"Numerical Model using MPS method on Droplet Breakup in Streaming Air", 31st Symposium on
Computational Fluid Dynamics, D09-3, 2017.

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

2-4

Elapsed Time per Case

1.00 minutes

 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

621.940.01

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

014.62

0.01

/data

146.23

0.00

/ltmp

2,994.79

0.23

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

Holistic approach for modeling general phenomena without relying
on particular preliminary knowledge
Report Number：R17EA1910
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4377/
Responsible Representative
Takeshi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Shogo Goto sgoto@chofu.jaxa.jp

Members
Masashi Kanamori, Shogo Goto

Abstract
It is important to gain a fast and accurate feedback from computational results in a design process. A
traditional way of Computational Fluid Dynamics (CFD) gives physically acceptable results at the costsof tremendous amount of computational resources and time. Our research group is therefore working ona machine-learning-based approach aimed at an innovative design tool.

Reasons for using of JSS2
A wide variety of data the amount of which should be as large as possible is required for high accuracy
prediction by machine learning. This conversely indicates poorly predicted results as a consequence of ashortage of data. The combination of the processing capability of JSS2 and a fast algorithm implemented
in our CFD code, FaSTAR can serve us a plenty of data within a short period of time and its data
productivity is necessary for the success of our research.

Achievements of the Year
We started our research with a learning of two-dimensional results, flowfields around a variety ofobjects like a circular cylinder (Fig. 1), an airfoil (Fig. 2) and so on. Then we obtained training data byprocessing such computational results above. Training processes were conducted on another computerwith Graphic Processing Unit (GPU) since GPU is only the way to achieve a machine learning in realistictime.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Flowfield around a circular cylinder( use grid part as learning data )Fig.2 Flowfield around an airfoil( use grid part as learning data )Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

2 - 64

Elapsed Time per Case

6.00 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

15,513.20

0.00

SORA-PP

594.250.01

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

006.13

0.00

/data

6,277.90

0.12

/ltmp

1,255.58

0.09

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

Development of Robust Numerical Scheme for Kerosene Turbulent Combustion
Report Number：R17EA1921
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4378/
Responsible Representative
Takashi Aoyama, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Shingo Matsuyama smatsu@chofu.jaxa.jp

Members
Shingo Matsuyama

Abstract
When carrying out a combustion simulation using a detailed reaction mechanism for a hydrocarbon
fuel, the number of chemical species to be considered and the stiffness due to a chemical reaction become
problems. In this study, by combining skeletal reaction mechanism and dynamic stiffness removal, wedeveloped a robust numerical scheme which enables combustion simulation with large scale detailed
reaction mechanism.

Reasons for using of JSS2
When performing turbulent combustion simulation on kerosene fuel widely used in gas turbine engines,
a large scale reaction model including over 100 chemical species and over 900 chemical reactions must
be solved. In order to perform LES and DNS for kerosene combustion, a huge number of grid pointsof the order of 100 million is necessary and the number of governing equations and chemical reactions
increase in proportion to the number of chemical species. Therefore, supercomputers are indispensable
for carrying out such large scale combustion simulations in this research.

Achievements of the YearIn this study, a skeletal reaction model and dynamic stiffness removal was applied to perform a
combustion simulation of a partially premixed flame of n-decane (Fig.1). Dynamic stiffness removal
showed that combustion simulation using a large scale detailed reaction mechanism can be performed
stably even with time-steps of 10-8 s that is more than 100 times larger than a characteristic time scale ofchemical reaction.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Snapshots of instantaneous contours of temperature (in K) for a partially premixed
flame of n-C10H22. The dashed line indicates the stoichiometric locations. Cited fromnon peer-reviewed paper [1]Publications
 Non peer-reviewed papers
1) Shingo Matsuyama, "Unsteady Simulation of Kerosene Partially Premixed Flame with Detailed
Chemical Reaction Model", proceedings of the fifty-fifth symposium (Japanese) on combustion,
E221, 2017.
2) Shingo Matsuyama, "Development of Turbulent Combustion Analysis Code CHARIOT",
proceedings of the 49th JSASS annual meeting, 2C05, 2018.
 Presentations
1) Shingo Matsuyama, "Unsteady Simulation of Kerosene Partially Premixed Flame with Detailed
Chemical Reaction Model", the fifty-fifth symposium (Japanese) on combustion, 2017.
2) Shingo Matsuyama, "Development of Turbulent Combustion Analysis Code CHARIOT", the 49th
JSASS annual meeting, 2018.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

25 - 75

Elapsed Time per Case

120.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.02
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

128,996.00

0.02

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

Numerical Analysis of Low-Speed Buffet using High-Resolution Scheme
Report Number：R17EA1935
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4379/
Responsible Representative
Takashi AOYAMA, Aeronautical Technology Directorate, Numerical Simulation Research Unit

Contact Information
Atsushi Hashimoto hashimoto.atsushi@jaxa.jp

Members
Takuya Aogaki, Atsushi Hashimoto, Keiichi Kitamura, Kanta Fukumoto, Ayano Inatomi,
Toshiaki Harada, Suguru Ogawa, Yuuya Takagi, Hiroyuki Takimoto, Hiroto Yaginuma

Abstract
Post Limiter has been improved to "Post Limiter 3(new)", and incorporated into JAXA's flow analysis
code "FaSTAR." Then, its performance has been demonstrated in several aerodynamic problems.
"Post Limiter 3(new)" and "HR-SLAU2" (numerical flux) are combined as a high-resolution scheme,
for flow analysis of low-speed buffet around NASA-CRM aircraft. This combination successfully
reproduced experimental data.

Reasons for using of JSS2
Expensive computations are carried out.
In addition, one of our objectives was to confirm that the high-resolution "FaSTAR" (the present
FaSTAR) successfully ran on JSS2.

Achievements of the Year
"Post Limiter 3 (new)" (Post Limiter 3 applied not only to primitive variables, but turbulent viscosity)
has been incorporated into "FaSTAR" (JAXA's flow analysis code), and its peformance has been
demonstrated in several aerodynamic problems. Then, high resolution schemes "Post Limiter 3 (new)"and "HR-SLAU2" (numerical flux) are employed to resolve complex flow physics of low-speed buffet
around aircraft (Fig.1). This combination successfully reproduced experimental data (Fig.2). These
results have been published in Journal of Computational Physics and reported in conferences.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Upper Surface Pressure Distribution on Aircraft (HR-SLAU2 + Post Limiter 3 (new))Fig.2 Pressure Distribusions at 28.3% Spanwise Cross-Section

Publications
 Peer-reviewed papers
1) Kitamura, K. and Hashimoto, A. "Simple a posteriori slope limiter (Post Limiter) for high resolution
and efficient flow computations," Journal of Computational Physics, Vol.341, 2017, pp. 313-340.
doi:10.1016/j.jcp.2017.04.002.
2) Kitamura, K., Ogawa, S., and Takahama, T. "Aerodynamic Improvements of Airfoils at Low
Reynolds Number by Moving Surface Method," JSASS Aerospace Technology Japan (in Japanese)(Accepted)3) Kitamura, K., Aogaki, T., Inatomi, A., Fukumoto, K., Takahama, T., Hashimoto, A. "Post Limiters
and Simple Dirty-Cell Detection for Three-Dimensional, Unstructured, (Unlimited) Aerodynamic
Simulations," AIAA Journal, (Under 2nd Review)

JAXA Supercomputer System Annual Report April 2017-March 2018

 Presentations
1) Takabayashi, K., Fukumoto, K., and Kitamura, K.: Computational Study on Rigid Disk-Gap-Band
Supersonic Parachute Aerodynamics, 31st International Symposium on Shock Waves (ISSW31),
Nagoya, Japan, Jul. 9-14, 2017.
2) Kitamura, K., Aogaki, T., Hashimoto, A. "Extension of Post Limiter to 3D Unstructured Grids and
Its Incorporation into FaSTAR," ANSS2017, 2017, Tokyo.
3) Kitamura, K., Aogaki, T., Inatomi, A., Fukumoto, K., Takahama, T., Hashimoto, A. "Post Limiters
and Simple Dirty-Cell Detection for 3D, Unstructured, (Unlimited) Aerodynamic Simulations,"
AIAA Aviation 2018 (to be presented in Atlanta, USA)

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

4 - 1024

Elapsed Time per Case

50.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.99
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

8,188,884.46

1.08

SORA-PP

7,011.75

0.09

SORA-LM

7,358.28

3.79

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

064.90

0.04

/data

1,227.38

0.02

/ltmp

13,281.26

1.00

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

8.89

0.38

*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

Development of 3D CFD core-software of automotive engine combustor
Report Number：R17EA1937
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4380/
Responsible Representative
Yasuhiro Mizobuchi, Aeronautical Technology Directrate, Numerical Simulation Research Unit

Contact Information
Yasuhiro Mizobuchi mizo@chofu.jaxa.jp

Members
Taisuke Nambu, Hiroki Yao, Shogo Yasuda, Yuichi Matsuo, Yasuhiro Mizobuchi,
Hiroyuki Abe, Manabu Hisida, Jin Kusaka, Akira Kikusato, Tsukasa Hori, Youichi Ogata,
Yoshimitsu Kohashi, Atsusi Fujino, Shun Ito, Daichi Obinata, Jun Hashimoto,
Ryohei Kirihara, Takuhito Kuwabara, Yasushi Noguchi, Kazuhiro Uehara, Taisuke Kayashima,
Yurina Maeda, Hiroyuki Sakai, Chikara Dodate, Shinji Nakamura, Takahiro Ishida,
Daisuke Tanaka, Takayuki Hori, Ryo Uchida, Takeshi Kuramoto, Takashi Kaminaga,
Satoshi Kawauchi, Daiki Miyai, Ryuichi Kaminaga, Tatsuya Kuboyama, Masato Kuchita,
Kenichi Tokunaga, Fumihiko Tanoue, Masayuki Suzuki, Kentaro Koyama, Noriyuki Ohi,
Kazuma Tago, Hisato Takeda, Yoshihiro Imaoka, Taketo Yamada, Junya Aono,
Yoshito Tsujimura, Tomohiro Nakayama, Yuhi Morii, Yoshinori Iwanaga, Taishin Kobae

Abstract
Enhancement of CAE utilization in automotive engine research by developing an engine combustion
simulation software that is sharable in Japan automotive research community.
https://www.jst.go.jp/sip/event/k01_hinoca/index.html

Reasons for using of JSS2
Massive parametric study, Massive-parallel large scale simulation

Achievements of the Year
Reproduction of engine port shape difference effects in steady port flow simulation. Achievement ofengine cycle simulation from intake to exhaust.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Effects of engine port configuration difference reproduced by HINOCA.

Fig.2 Engine cycle simulation from intake to exhaust.

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Presentations
1) A. Kikusato et al., "Numerical Analysis on Flame Propagation in an Automobile Engine," 49th Flluiid
Dynamiics Confference/35th Aerospace Numeriicall Siimullatiion Symposiium, Jun. 28, 2017.
2) D. Miyai et al., "Wall Reflection/Deposition Model of Spray in Immersed Boundary Model," 49th
Flluiid Dynamiics Confference/35th Aerospace Numeriicall Siimullatiion Symposiium, Jun. 28,
2017.
3) Y. Matsuo et al., "Application of an adaptive mesh refinement method to the analysis of flow inside
an engine cylinder," 49th Flluiid Dynamiics Confference/35th Aerospace Numeriicall Siimullatiion
Symposiium, Jun. 28, 2017.
4) T. Nambu et al., "Validation of LES flow solver using immersed boundary method through analysesof curved duct flow," 49th Flluiid Dynamiics Confference/35th Aerospace Numeriicall Siimullatiion
Symposiium, Jun. 28, 2017.
5) T. Hori, Y. Mizobuchi, "Spark Ignition Model for 3D Spark-Ignition Engine with Spark Channel
Elongation," 49th Flluiid Dynamiics Confference/35th Aerospace Numeriicall Siimullatiion
Symposiium, Jun. 28, 2017.
6) Y. Mizobuchi, "Development of engine combustion simulation software HINOCA," JSME RC276
2nd meeting, Sept. 21, 2017.
7) D. Miyai et al., "Steady State Port Flow Calculation with RANS HINOCA," 28th Internal
Combustion Engine Symposium, Dec. 6, 2017.
8) R. Kaminaga et al., "Steady State Port Flow Calculation with LES HINOCA," 28th Internal
Combustion Engine Symposium, Dec. 6, 2017.
9) Y. Mizobuchi, "Goals and functions of engine combustion simulation software HINOCA," JSME
workshop, Jan. 19, 2018.
 URLs for the Research Results on the Web1) https://www.jst.go.jp/sip/event/k01_hinoca/index.html

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

2 - 600

Elapsed Time per Case

500.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 9.75
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

74,935,495.13

9.80

SORA-PP

1,007,804.54

12.62

SORA-LM

178.52

0.09

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

1,392.84

0.97

/data

488,976.63

9.04

/ltmp

45,143.32

3.40

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

38.17

1.64

*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

Improvement of simulation of internal flow of turbomachine
Report Number：R17EA2111
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4381/
Responsible Representative
Takashi Yamane, Propulsion Research Unit, Aeronautical Technology Directorate

Contact Information
Junichi Kazawa kazawa.junichi@jaxa.jp

Members
Junichi Kazawa, Takahiro Kawahara

Abstract
In the turbomachine internal flow, the separation on the blade surface and the behavior of the vortex
have a large influence on the aerodynamic performance. In numerical analysis using RANS, it is difficult
to simulate the separation and vortex in detail, so we analyze using LES for predicting highly accurate
aerodynamic performance, and improve accuracy of aerodynamic performance prediction.

Reasons for using of JSS2
Since the mesh required for LES analyses becomes large scale, supercomputers are necessary.

Achievements of the Year
Numerical calculations by UPACS developed by JAXA were performed on a vaneless diffuser
centrifugal compressor (Krain, 1988) in which the geometry and measurement results (performance
curve, static pressure distribution on the wall surface, L2F in the cross section of the flow passage) are
published. Computation by RANS and LES at two or more operating points is performed for two kindsof mesh, coarse (5 M points) and fine (18 M points), with imposing a periodic boundary condition in
the circumferential direction. In the numerical prediction of the performance curve, the loss tends to belower than the experimental value and the estimation performance tends to be overestimated comparedwith the experimental data. But in general aprediction results by LES are closer to the experiment data
than the RANS.It is suggested that LES captures the generation and loss of vortices more accurately than
RANS. On the other hand, the numerical prediction result overestimates the performance even in LES
on the high rotating speed and high pressure ratio side. It is a future task to clarify the cause as a result.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Centrifugal compressor shape and mesh

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.2 Performance curve of centrifugal compressor

Fig.3 Entropy distribution (animation)

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

51 - 58

Elapsed Time per Case

165.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.13
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

199,682.19

2.50

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

010.22

0.01

/data

960.49

0.02

/ltmp

2,092.63

0.16

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

Development of CFD technology to support design of aircraft combustor with realconfiguration.
Report Number：R17EA2117
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4382/
Responsible Representative
Takashi Yamane, Aeronautical Technology Directorate, Propulsion Research Unit

Contact Information
Mitsumasa Makida makida.mitsumasa@jaxa.jp

Members
Mitsumasa Makida(JAXA), Naoki Nakamura(ASIRI)

Abstract
In this research, we aim to obtain design methods for development of aircraft combustors with realconfiguration, which estimate dispersion of the fuel droplets, evaporation, and combustion processes.

Reasons for using of JSS2
It is important to do parametric case study with slightly different geometry, and each case with sprayand combustion needs large scale simulation. To conduct such simulation and visualization effectively,
we use the super computer with high parallelization efficiency.

Achievements of the YearIn this fiscal year, we integrate real gas effect, fuel evaporation and chemical reaction model into thebase solver, which enabled to simulate the distribution of fuel spray, fuel vapor and chemical reaction
rate near the fuel nozzle with realistically complicated configuration.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Disrtibution of fuel spray, fuel vapor and reaction rate near fuel nozzle

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelizatio

Number of Processes

120

Elapsed Time per Case

300.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.31
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

2,536,622.63

0.33

SORA-PP

4,300.70

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

211.66

0.15

/data

9,391.05

0.17

/ltmp

1,519.10

0.11

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.14

0.01

*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

Improvement of numerical analysis for internal flow with complicated configuration inside
aero-engine.
Report Number：R17EA2120
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4383/
Responsible Representative
Takashi Yamane, Aeronautical Technology Directorate, Propulsion Research Unit

Contact Information
Mitsumasa Makida makida.mitsumasa@jaxa.jp

Members
Mitsumasa Makida, Shunji Enomoto, Junichi Kazawa, Atsushi Hashimoto, Takashi Ishida,
Shigeru Kuchiishi, Taisuke Nambu(JAXA), Hiroki Ugajin, Tanaka Uhi, Yani Naoki(IHI)

Abstract
Unstructured-grid flow solver FaSTAR and grid generator BOXFUN are applied to aero-engine
elements with complicated configuration (such as linear and rotating cascades). Through the calculation,these programs are tested and investigated for the deficiency and future issue for improvement of
accuracy.
http://www.aero.jaxa.jp/eng/research/basic/numerical/analysis-tool/

Reasons for using of JSS2
Aiming to do large scale calculation in the future, programs should be tested under the same
computational environment.

Achievements of the Year
Numerical calculation by FaSTAR was applied to the T106A cascade with which a lot of CFD results
and experimental measurement data are published. Fig.1 shows result of calculation without turbulencemodel, and we can see unsteady result which shows the transition process from laminar flow boundary
layer separation to turbulent flow. (Inlet angle: 45 degree, Reynolds number based on chord length: 60E4,
Mach number: 0.4)

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Mach number distribution of T106A cascade flow

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelizatio

Number of Processes

512

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

11,856.12

0.00

SORA-PP

387.31

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

045.94

0.03

/data

11,358.09

0.21

/ltmp

3,162.08

0.24

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

9.54

0.09

*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 on High Speed Propulsion Systems using Hydrogen Fuel
Report Number：R17EA2121
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4384/
Responsible Representative
Takashi Yamane, Aeronautical Technology Directorate, Propulsion Research Unit

Contact Information
Hideyuki Taguchi taguchi.hideyuki@jaxa.jp

Members
Hideyuki Taguchi, Motoyuki Hongoh, Masaharu Hiruma,Jun Butsuen, Masahiro Uji, Yuki Kayama

Abstract
This research aims at the demonstration of the thrust control method of a hypersonic pre-cooled
turbojet engine using liquid hydrogen fuel and the aircraft / propulsion integrated control method. We
acquire the control characteristics of the hypersonic integrated control experiment aircraft to establish
the aircraft / propulsion integrated control method taking into account the mutual interference ofhypersonic airframe and hypersonic engines.

In addition to defining the required specifications ofhypersonic aircraft, we present the design specifications of the hypersonic experimental aircraft forcarrying out flight demonstration of hypersonic pre-cooled turbojet engine.
http://www.aero.jaxa.jp/eng/research/frontier/hst/

Reasons for using of JSS2
We need a long calcularion time to obtaine the aerodynamic characteristics of the overall hypersonicexperimental aircraft by CFD analyses.

Achievements of the Year
(1) Aerodynamics of the Hypersonic Cruise Experimental Aircraft was evaluated by CFD analyses.
(Fig.1)(2) Aerodynamics of the High Mach Integreted Control Experimental Aircraft was evaluated by CFD
analyses. (Fig.2, Fig. 3)

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Hypersonic Cruise Experimental Aircraft (Cp Contour, Mach 7, AoA=0deg)

Fig.2 Hypersonic Control Experimental Aircraft (Cp Contour, Mach 5, AoA=15deg)

Fig.3 High Mach Integrated Control Experimental Aircraft (Mach Contour, Mach 5, AoA=0deg)

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 ■ Non peer-reviewed papers
1) Hiruma, M., Hirotani, T., Hongoh, M., Taguchi, T. and Tezuka, A., "Aerodynamic Evaluation ofHypersonic Cruise Experimental Aircraft," 61th Joint Conference on Space Science and Technology,
2017.
2) Butsuen, J., Hirotani, T., Taguchi, T., Hongoh, M., Tezuka, A. and Hiruma, M, "Lateral and
Directional Aerodynamics Evaluation of High Mach Integrated Control Experimental Aircraft,"
55th Aircraft Symposium, 2017.
 Presentations
1) Hiruma, M., Hirotani, T., Hongoh, M., Taguchi, T. and Tezuka, A., "Aerodynamic Evaluation ofHypersonic Cruise Experimental Aircraft," 61th Joint Conference on Space Science and Technology,
2017.
2) Butsuen, J., Hirotani, T., Taguchi, T., Hongoh, M., Tezuka, A. and Hiruma, M, "Lateral and
Directional Aerodynamics Evaluation of High Mach Integrated Control Experimental Aircraft,"
55th Aircraft Symposium, 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

60 - 144

Elapsed Time per Case

72.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.84
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

6,527,843.25

0.87

SORA-PP

6,058.37

0.08

SORA-LM

6,584.94

3.39

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

2,145.77

1.49

/data

53,710.96

0.99

/ltmp

8,789.07

0.66

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

System Operation of the Digital/Analog-Hybrid Wind Tunnel (DAHWIN)
Report Number：R17EA2405
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4563/
Responsible Representative
Shigeru Kuchi-Ishi, Aeronautical Technology Directorate, Aerodynamics Research Unit

Contact Information
Shigeru Kuchi-Ishi shigeruk@chofu.jaxa.jp

Members
Hiroyuki Kato, Shigeru Kuchiishi, Makoto Ueno, Atsushi Hashimoto, Yuichi Matsuo,
Kanako Yasue, Suzuki Kohji

Abstract
Through the operation of the JAXA Digital/Analog-Hybrid Wind Tunnel (DAHWIN), we aim torealize the complementary use of Experimental Fluid Dynamics (EFD) and Computational Fluid
Dynamics (CFD). Specifically, a series of DAHWIN functions (e.g. CFD before wind tunnel testing, test
preparation using pre-CFD data, real time EFD/CFD data monitoring, and EFD/CFD data integration)
are served to the system users.
http://www.aero.jaxa.jp/eng/research/basic/aerodynamic/dahwin/

Reasons for using of JSS2DAHWIN performs a number of high-fidelity and large-scaled computations (3D RANS analysis)
based on the JAXA 2m x 2m transonic wind tunnel testing, and then the use of JSS2 is necessary.

Achievements of the YearFor the CFD analysis using DAHWIN, the system was applied to a total of two JAXA 2m x 2m transonicwind tunnel tests.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 CFD results for the AGARD-B model using DAHWIN

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

16 - 96

Elapsed Time per Case

1.25 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.02
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

5,099.41

0.00

SORA-PP

28.83

0.00

SORA-LM

56.49

0.03

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

649.68

0.45

/data

22,918.60

0.42

/ltmp

7,525.62

0.57

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.71

0.03

*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

aFJR high efficiency fan technology development
Report Number：R17EA2710
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4385/
Responsible Representative
Toshio Nishizawa, aFJR Project Team, Aeronautical Technology Directorate

Contact Information
Junichi Kazawa kazawa.junichi@jaxa.jp

Members
Junichi Kazawa, Shunji Enomoto, Toshio Nishizawa, Susumu Kato, Kenshi Yamashita

Abstract
The purpose of aFJR project is to advance research on jet engine component technologies so thatJapanese manufacturers can join more effectively in international joint-development projects on nextgeneration jet engines. To compensate for increasing fan diameter, we are developing lightweight fan
blades that have higher aerodynamic efficiency by applying advanced simulation technology andcomposite materials evaluation technology.
For the development of high efficiency laminar flow fan blade technology in aFJR project,

it isnecessary to investigate the possibility that laminar flow fan blade design adversely affects fan flutter.
http://www.aero.jaxa.jp/eng/research/ecat/afjr/

Reasons for using of JSS2
Flutter simulation is useful for increasing the certainty of aFJR project and super-computers are
required for this type of transition simulation.

Achievements of the YearFor the fan blades used in the demonstration test, the flutter occurece point in a wide range of operation
area was predicted. This made it possible to avoid flutter in the demonstration test.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Natural vibration mode of fan blade

Fig.2 Mach number distribution

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.3 Flutter occurrence point prediction result

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

96

Elapsed Time per Case

120.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.58
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

6,831,961.84

0.91

SORA-PP

742,527.45

9.30

SORA-LM

0.00

0.00

SORA-TPP

267,950.51

29.90

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

027.70

0.02

/data

7,194.98

0.13

/ltmp

3,915.55

0.30

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

9.63

0.41

*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

Structural analysis of Composite Fan blade
Report Number：R17EA2720
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4386/
Responsible Representative
Toshio Nishizawa, Aeronautical Technology Directorate, aFJR project teamContact Information
Masahiro Hojo hojo.masahiro@jaxa.jp

Members
Masahiro Hojo, Kenshirou Kondou, Shota Sadamoto, Tomoaki Watanabe, Takuya Ando, Koji Miyazaki

Abstract
The purpose of aFJR project is to advance research on jet engine component technologies so thatJapanese manufacturers can join more effectively in international joint-development projects on nextgeneration jet engines. The technology of the weight reduction of composite fan blade is researched in
the aFJR project.
http://www.aero.jaxa.jp/eng/research/ecat/afjr/

Reasons for using of JSS2
The hollow composite fan blade was designed based on the bird strike simulation results using JSS2.

Achievements of the Year
Figure 1 shows the analysis result of the bird strike simulation of hollow composite fan blade. The
dynamic behavior of fan blade and the strain time histories were very close to those of the demonstration
test result.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 The bird strike simulation of hollow composite fan blade (a) t = 0.3 ms

Fig.2 The bird strike simulation of hollow composite fan blade (b) t = 0.9 ms

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.3 The bird strike simulation of hollow composite fan blade (c) t = 1.2 ms

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

128

Elapsed Time per Case

50.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.20
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

1,364,797.48

0.18

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

182.79

0.13

/data

56,745.24

1.05

/ltmp

5,533.86

0.42

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

6.93

0.29

*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

aFJR light weight sound absorption liner technology development
Report Number：R17EA2740
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4387/
Responsible Representative
Toshio Nishizawa, Aeronautical Technology Directorate, aFJR project teamContact Information
Shunji ENOMOTO enomoto.shunji@jaxa.jp

Members
Shunji ENOMOTO, Tatsuya ISHII, Daisuke Sasaki, Hidemi Toh, Tsubasa Iwafune,
Yusuke Akamisaka, Takuma Kanda, Ryo Inagaki, Hitoshi Morita

Abstract
The purpose of aFJR project is to advance research on jet engine component technologies so thatJapanese manufacturers can join more effectively in international joint-development projects on nextgeneration jet engines. To compensate for increasing fan diameter, we are developing lightweight fan
blades that have higher aerodynamic efficiency by applying advanced simulation technology andcomposite materials evaluation technology.
For the development of lightweight sound absorbing liner technology, we developed a technology tosimulate sound waves absorbed by sound absorbing liners and devise a shape with higher absorption rate.
http://www.aero.jaxa.jp/eng/research/ecat/afjr/

Reasons for using of JSS2
The calculation is LES with a large amount of computation and storage usage. It was necessary to use
SORA-PP, TPP, and SORA-FS.

Achievements of the Year
Numerical simulation method of sound absorbing liner with glazing flow was studied by using UPACSLES which is an analytical code with less attenuation of sound waves using a 6th order compact scheme.
Two-dimensional laminar flow was assumed for calculation. Fig. 1 shows the sound pressure. Sound
waves propagating from the left to the right in the figure are absorbed by sound absorbing cells installedat the lower center of the figure.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Sound pressure

Publications
 Presentations
1) Shunji ENOMOTO, Tatsuya Ishii, Yusuke Akamisaka, Hidemi Toh, "Numerical analysis of soundabsorbing liner with glazing flow", 50th Fluid Dynamics Conference / 35th Aerospace Numerical
Simulation Symposium, 2018

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 - 24

Elapsed Time per Case

40.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.24
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

172,878.44

2.16

SORA-LM

0.00

0.00

SORA-TPP

100,091.06

11.17

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

486.37

0.34

/data

21,003.73

0.39

/ltmp

11,914.07

0.90

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

9.39

0.40

*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

aFJR Lightweight low-pressure turbine technology development
Report Number：R17EA2750
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4388/
Responsible Representative
Toshio Nishizawa, aFJR Project Team, Aeronautical Technology Directorate

Contact Information
Junichi Kazawa kazawa.junichi@jaxa.jp

Members
Junichi Kazawa, Toshio Nishizawa, Yasuo Horiguchi

Abstract
The purpose of aFJR project is to advance research on jet engine component technologies so thatJapanese manufacturers can join more effectively in international joint-development projects on nextgeneration jet engines. In order to suppress the weight increase of the low pressure turbine, we develop
ultra lightweight low pressure turbine technology applying heat resistant composite (ceramic based
composite material (CMC)) by developing over-rotation prevention design technology and highreliability evaluation. As a part of the evaluation of high reliability, we will develop flutter boundary
prediction technology considering structural characteristics and flutter prediction technology of CMC
made low pressure turbine blade , after confirming the prediction accuracy of flutter occurrence point of
low pressure turbine blade with comparison of experiment and CFD.
http://www.aero.jaxa.jp/eng/research/ecat/afjr/

Reasons for using of JSS2
Since flutter analyses have many parameters and the number of analysis cases is enormous, it isnecessary to use supercomputers to obtain results within a limited period of time.

Achievements of the Year
We analyzed the flutter characteristics when the material of the blade was changed from SUS to CMC
using the airfoil used in the experiments in last year. It was confirmed that flutter characteristics analyses
were possible also for CMC made blades, and flutter characteristics for blades of different materials could
be grasped.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 static pressure distribution on wall

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

24 - 48

Elapsed Time per Case

30.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.16
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.85

0.00

SORA-PP

238,282.78

2.98

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

067.44

0.05

/data

3,897.80

0.07

/ltmp

1,441.59

0.11

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

Structural Analysis of Low Pressure Turbine
Report Number：R17EA2751
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4389/
Responsible Representative
Toshio Nishizawa, Aeronautical Technology Directorate, aFJR project teamContact Information
Masahiro Hojo hojo.masahiro@jaxa.jp

Members
Kenshirou Kondou, Shota Sadamoto, Masahiro Hojo, Takuya Ando, Tomoaki Watanabe, Koji Miyazaki

Abstract
The purpose of aFJR project is to advance research on jet engine component technologies so thatJapanese manufacturers can join more effectively in international joint-development projects on nextgeneration jet engines. Application of a Ceramic Matrix Composite (CMC) to low pressure turbine blade
material is conducted to reduce the engine weight in the aFJR project.
http://www.aero.jaxa.jp/eng/research/ecat/afjr/

Reasons for using of JSS2
The CMC low pressure turbine blade was designed based on the analysis results using JSS2. The CMC
blade design methodology was demonstrated experimentally.

Achievements of the Year
Figure shows the fracture analysis result of the cascade of CMC low pressure turbine blades at the
moment of contact with the cascade of stator vanes. The fracture mode of the cascade of CMC blades
could be analyzed.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 The fracture analysis of the cascade of CMC blades

Publications
 Non peer-reviewed papers
1) J. Kitagawa, S. Fukushige, T. Yoden, M. Hojo, Development of Impact Fracture Model of Ceramics
Matrix Composite based on Impact Tests, 68th Aeroballistic Range Association Meeting, (2017),CA.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

128 - 256

Elapsed Time per Case

200.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.69
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

5,256,874.22

0.70

SORA-PP

0.00

0.00

SORA-LM

11,859.73

6.11

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

201.86

0.14

/data

56,935.97

1.05

/ltmp

9,440.11

0.71

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

6.93

0.30

*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

Computational Simulations for Aircraft Modification Design in the FQUROH Project
Report Number：R17EA2800
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4390/
Responsible Representative
Kazuomi Yamamoto, FQUROH Project Team, Aeronautical Technology Directorate

Contact Information
Kazuomi Yamamoto yamamoto.kazuomi@jaxa.jp

Members
Kazuomi Yamamoto, Yasushi Ito, Takehisa Takaishi, Mitsuhiro Murayama, Ryotaro Sakai,
Tohru Hirai, Kentaro Tanaka, Kazuhisa Amemiya, Gen Nakano, Takashi Ishida

Abstract
The FQUROH project aims at raising the technical maturity level of the noise reduction technology
for high-lift devices and landing gear, which draws international attention to reduce noise in areas aroundairports, to a level applicable to future development of aircraft and related equipment. This contributes
to reduction of aircraft noise in local communities around the airport and airline operating costs by
reducing landing fee. One of the objectives of the FQUROH project is to verify the feasibility of practicalnoise reduction concepts and design methods based on advanced computational simulations throughmodification of aircraft. Computational simulations were performed as part of the FQUROH project tounderstand Reynolds number effects resulting from wind tunnel testing and to select low-noise andmeasuring devices that did not affect the flight performance of experimental aircraft in an expected flightenvelop.
http://www.aero.jaxa.jp/eng/research/ecat/fquroh/

Reasons for using of JSS2
The JSS2 enabled a large number of high-fidelity computational simulations with aerodynamicallyimportant details in several flight configurations (flap deflection angle settings, landing gear positions,etc.) in the expected flight envelop (i.e., needs to consider several angles of attack, sideslip angles, etc.).
The aerodynamic effect of low-noise and measuring devices was able to be evaluate and quantified, which
was difficult only with wind tunnel tests.

JAXA Supercomputer System Annual Report April 2017-March 2018

Achievements of the YearFor the second flight demonstration on airframe noise reduction technologies, RANS results confirmedthat the flight characteristics, flight performance and structure of JAXA's jet research aircraft, "Hisho,"were not significantly affected by low-noise devices for the flaps and landing gear and pressure belts on
the right outboard flap. RANS simulations were also performed for the JAXA Standard Model (JSM) to
understand the aerodynamic characteristics of a high-lift configuration with a slat, such as flow
separation induced by slat brackets.

Fig.1 Surface stream lines and x component of vorticity on cross-flow cross-sections aroundthe flaps of Hisho gear-down, 35 degrees flap deflection angle configuration with flap
and landing-gear low-noise devices and pressure belts on the right outboard flap f

Fig.2 Different stall patters with and without slat brackets of JSM wing/body configuration(images showing skin friction distributions and large flow separation indicated bywhite dashed lines): (a) stall caused by side-of-body flow separation without slat bra

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Non peer-reviewed papers
1) Ito, Y., Murayama, M., Yamamoto, K. and Tanaka, K., "High-Fidelity Aerodynamic Analysis of
Aircraft in Various Configurations with MEGG3D," AIAA Paper 2017-3804, 23rd AIAA
Computational Fluid Dynamics Conference, 2017, DOI: 10.2514/6.2017-3804.
2) Yamamoto, K., Takaishi, T., Murayama, M., Yokokawa, Y., Ito, Y., Arizono, H., Sakai, R., Shoji, H.,
Ueno, Y., Isotani, K., Lee, H.-H., Inoue, T. and Kumada, T., "FQUROH: A Flight Demonstration
Project for Airframe Noise Reduction Technology - the 1st Flight Demonstration," AIAA Paper
2017-4029,

23rd

AIAA/CEAS

Aeroacoustics

Conference,

Denver,

CO,

2017,

DOI:

10.2514/6.2017-4029.
3) Yokokawa, Y., Takaishi, T., Ura, H., Kohzai, M., Murayama, M., Ito, Y., Yamamoto, K., Isotani, K.,
Ueno, Y. and Hayama, K., "Acoustic Wind Tunnel Test with 18% scale Half-span Model toward
FQUROH Flight Demonstration," AIAA Paper 2017-4032, 23rd AIAA/CEAS Aeroacoustics
Conference, 2017, DOI: 10.2514/6.2017-4032.
4) Ito, Y., Murayama, M., Yokokawa, Y., Yamamoto, K., Tanaka, K., Hirai, T., Yasuda, H., Tajima, A.
and Ochi, A., "Japan Aerospace Exploration Agency's and Kawasaki Heavy Industries' Contribution
to the Third High Lift Prediction Workshop," AIAA Paper 2018-1034, 2018 AIAA Aerospace
Sciences Meeting, Kissimmee, FL, 2018, DOI: 10.2514/6.2018-1034.
 Presentations
1) Ito, Y., Murayama, M., Yamamoto, K., Tanaka, K. and Hirai, T., "TAS Code Results for the ThirdHigh Lift Prediction Workshop," Presented at the 3rd AIAA CFD High Lift Prediction Workshop,
Denver, CO, 2017.
 URLs for the Research Results on the Web1) 3rd AIAA CFD High Lift Prediction Workshop (HiLiftPW-3), https://hiliftpw.larc.nasa.gov/

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

432

Elapsed Time per Case

25.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.79
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

14,807,705.37

1.96

SORA-PP

6,600.57

0.08

SORA-LM

8.12

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

064.49

0.04

/data

9,930.81

0.18

/ltmp

2,682.33

0.20

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

177.48

7.63*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 on Airframe Noise Reduction Design in the FQUROH Project
Report Number：R17EA2801
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4391/
Responsible Representative
Kazuomi Yamamoto, FQUROH Project Team, Aeronautical Technology Directorate

Contact Information
Kazuomi Yamamoto yamamoto.kazuomi@jaxa.jp

Members
Kazuomi Yamamoto, Yasushi Ito, Takehisa Takaishi, Mitsuhiro Murayama, Ryotaro Sakai,
Tohru Hirai, Kentaro Tanaka, Kazuhisa Amemiya, Gen Nakano, Takashi Ishida

Abstract
This research is being carried out as part of the FQUROH project aimed at raising the technicalmaturity level of the noise reduction technology for high-lift devices and landing gear, which draws
international attention to reduce noise in areas around airports, to a level applicable to future
development of aircraft and related equipment. This contributes to reduction of aircraft noise in local
communities around the airport and airline operating costs by reducing landing fee. One of the objectivesof the FQUROH project is to verify the feasibility of practical noise reduction concepts and design
methods based on advanced computational simulations based on large-scale Reynolds-averaged NavierStokes (RANS) simulations and more advanced computational simulations, such as Large/Detached
Eddy Simulations (LES/DES).
http://www.aero.jaxa.jp/eng/research/ecat/fquroh/

Reasons for using of JSS2
The JSS2 was used to understand detailed physics of noise generation, to optimize noise reduction
designs. The FQUROH project aims to accelerate technology maturity of airframe noise reduction
methods using advanced computational simulations on the JSS2's high performance computing platform
and to demonstrate the high-fidelity design technologies through flight tests. Computational simulations
using the JSS2 made it possible to design low-noise devices by understanding detailed physicalphenomena, which was difficult only with wind tunnel tests.

JAXA Supercomputer System Annual Report April 2017-March 2018

Achievements of the YearIn the FQUROH project, unsteady flow simulations based on Delayed Detached Eddy Simulations(DDES) were conducted to improve noise reduction designs for slats, one of the major airframe noise
sources. Two kinds of noise reduction devices have been investigated using DDES around representative
parts of an actual aircraft wing with a limited span length. They were effective in DDES and wind tunnel
tests using a scaled model. The aerodynamic and aeroacoustic effect of structural constrains due to small
scale devices were also evaluated by computational fluid dynamics prior to the wind tunnel tests to reduce
their risks.
In our simulations based on original DDES proposed by Spalart, it was confirmed that mixing of theshear layer from the slat cusp was delayed, which led to overestimation of acoustic peaks characteristic
to the slat noise. Such the delay has been pointed out by several researchers and they also have proposed
new definitions of subgrid length scale in DDES in order to solve this problem. In this research fivesubgrid length scales ever proposed have been tested through aeroacoustic simulations for the 30P30N
and DLR F16 three-element high-lift airfoils known as benchmark problems for the slat noise. Mixing of
the shear layer has been facilitated and flow statistics along the shear layer have been improved by using
the subgrid length scales proposed by Deck or Shur in which the direction of vortex is taken into
consideration. Due to geometrical constraints, computational meshes around the slats tend to stretch
along spanwise direction. It has been found that the subgrid length scales focusing on cell spacings
contributing to resolving vortices are needed to avoid possible negative effect caused by anisotropic cells
around the slats.

Fig.1 Comparison of isosurfaces of Q-criterion around the slat of DLR F16 airfoil (coloredby Mach number) with different subgrid length scales

JAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Non peer-reviewed papers
1) Yamamoto, K., Takaishi, T., Murayama, M., Yokokawa, Y., Ito, Y., Arizono, H., Sakai, R., Shoji, H.,
Ueno, Y., Isotani, K., Lee, H.-H., Inoue, T. and Kumada, T., "FQUROH: A Flight Demonstration
Project for Airframe Noise Reduction Technology - the 1st Flight Demonstration," AIAA Paper
2017-4029,

23rd

AIAA/CEAS

Aeroacoustics

Conference,

Denver,

CO,

2017,

DOI:

10.2514/6.2017-4029.
2) Sakai, R., Ishida, T., Murayama, M., Ito, Y. and Yamamoto, K., "Effect of Subgrid Length Scale in
DDES on Aeroacoustic Simulation around Three-Element Airfoil," AIAA Paper 2018-0756, 2018
AIAA Aerospace Sciences Meeting, Kissimmee, FL, 2018, DOI: 10.2514/6.2018-0756.

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

1728

Elapsed Time per Case

130.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 5.81
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

48,916,266.87

6.46

SORA-PP

36,243.83

0.45

SORA-LM

26.32

0.01

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

064.49

0.04

/data

8,954.25

0.17

/ltmp

2,682.33

0.20

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

177.48

7.63*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

Cooperative Research on High Lift Devices in the FQUROH Project
Report Number：R17EA2810
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4392/
Responsible Representative
Kazuomi Yamamoto, FQUROH Project Team, Aeronautical Technology Directorate

Contact Information
Kazuomi Yamamoto yamamoto.kazuomi@jaxa.jp

Members
Akio Ochi, Kazuhide Isotani, Yousuke Ueno, Hidemasa Yasuda, Yuta Tsuchimoto,Kazuomi Yamamoto, Yasushi Ito, Mitsuhiro Murayama, Ryotaro Sakai

Abstract
This collaborative research is being carried out as part of the FQUROH project aimed at raising thetechnical maturity level of the noise reduction technology for high-lift devices, which draws international
attention to reduce noise in areas around airports, to a level applicable to future development of aircraft
and related equipment. This contributes to reduction of aircraft noise in local communities around the
airport and airline operating costs by reducing landing fee.
http://www.aero.jaxa.jp/eng/research/ecat/fquroh/

Reasons for using of JSS2
The JSS2 enabled low-noise devices to be designed based on Reynolds-averaged Navier-Stokes
simulations and more advanced computational simulations, such as large eddy simulations, using
unsteady computational fluid dynamics software, "Cflow," developed by the Kawasaki Heavy Industries(KHI). Computational simulations using the JSS2 made it possible to design low-noise devices by
understanding detailed physical phenomena, which was difficult only with wind tunnel tests.

Achievements of the YearFor the second flight demonstration on airframe noise reduction technologies with JAXA's jet research
aircraft "Hisho," KHI modified the KHI-designed flap noise reduction devices called "Small Barriers," byadjusting their location, size and number. The effect of the modified devices was examined with the KHIdeveloped unsteady computational fluid dynamics software, "Cflow." It was found that the modified
devices contributed to further reducing flap noise.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Lambda2 isosurface colored by vorticity magnitude around the most outboard flap tipof "Hisho" based on unsteady CFD analysis

Publications
 Non peer-reviewed papers
1) Yamamoto, K., Takaishi, T., Murayama, M., Yokokawa, Y., Ito, Y., Arizono, H., Sakai, R., Shoji, H.,
Ueno, Y., Isotani, K., Lee, H.-H., Inoue, T. and Kumada, T., ""FQUROH: A Flight Demonstration
Project for Airframe Noise Reduction Technology - the 1st Flight Demonstration,"" AIAA Paper
2017-4029,

23rd

AIAA/CEAS

10.2514/6.2017-4029.

Aeroacoustics

Conference,

Denver,

CO,

2017,

DOI:

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

2048

Elapsed Time per Case

80.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.12
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA754,953.51

0.10

SORA-PP

22.06

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

061.84

0.04

/data

13,815.67

0.26

/ltmp

7,559.72

0.57

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

89.59

3.85

*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

Cooperative Research on Landing Gear in the FQUROH Project
Report Number：R17EA2820
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4393/
Responsible Representative
Kazuomi Yamamoto, FQUROH Project Team, Aeronautical Technology Directorate

Contact Information
Kazuomi Yamamoto yamamoto.kazuomi@jaxa.jp

Members
Akihisa Shimada, Kazuomi Yamamoto, Yasushi Ito, Mitsuhiro Murayama, Ryotaro Sakai

Abstract
This collaborative research is being carried out as part of the FQUROH project aimed at raising thetechnical maturity level of the noise reduction technology for landing gear, which draws international
attention to reduce noise in areas around airports, to a level applicable to future development of aircraft
and related equipment. This contributes to reduction of aircraft noise in local communities around the
airport and airline operating costs by reducing landing fee.
http://www.aero.jaxa.jp/eng/research/ecat/fquroh/

Reasons for using of JSS2
The JSS2 enabled low-noise devices to be designed based on Reynolds-averaged Navier-Stokes
simulations, thermo-fluid coupling simulations and more advanced computational simulations, such aslarge eddy simulations, using Siemens STAR-CCM+. Computational simulations using the JSS2 madeit possible to design low-noise devices by understanding detailed physical phenomena, which wasdifficult only with wind tunnel tests and tests with an actual aircraft.

Achievements of the Year
Computational simulations of brake cooling was conducted for baseline and low-noise configurationsof the main landing gear of JAXA's jet research aircraft, "Hisho," under a condition similar to that during
the temperature measurement in Noto Airport, Ishikawa, Japan during the second flight demonstration
on airframe noise reduction technologies. No significant influence was observed in time required forbrake cooling with the low-noise configuration, which had a porous plate mounted between the tires andthe wheels had no holes.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Initial temperature distribution (without porous plate and with wheel holes)

Fig.2 Initial temperature distribution (with porous plate and without wheel holes)

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.3 Time history of brake temperature after brake operation

Publications
 Non peer-reviewed papers
1) Yamamoto, K., Takaishi, T., Murayama, M., Yokokawa, Y., Ito, Y., Arizono, H., Sakai, R., Shoji, H.,
Ueno, Y., Isotani, K., Lee, H.-H., Inoue, T. and Kumada, T., "FQUROH: A Flight Demonstration
Project for Airframe Noise Reduction Technology - the 1st Flight Demonstration," AIAA Paper
2017-4029,

23rd

AIAA/CEAS

Aeroacoustics

Conference,

Denver,

CO,

2017,

DOI:

10.2514/6.2017-4029.
2) Takaishi, T., Inoue, T., Lee, H.-H., Murayama, M., Yokokawa, Y., Ito, Y., Kumada, T. andYamamoto, K., "Noise Reduction Design for Landing Gear toward FQUROH Flight
Demonstration," AIAA Paper 2017-4033, 23rd AIAA/CEAS Aeroacoustics Conference, Denver,
CO, 2017, DOI: 10.2514/6.2017-4033.

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

120

Elapsed Time per Case

12.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.08
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

0.00

0.00

SORA-PP

79,527.35

1.00

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

057.07

0.04

/data

6,836.68

0.13

/ltmp

6,583.16

0.50

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

89.59

3.85

*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 and development of applied fundamental technology
Report Number：R17EA3201
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4394/
Responsible Representative
Takeshi Ito, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation HubCenterContact Information
Atsushi Hashimoto hashimoto.atsushi@jaxa.jp

Members
Hamidreza Kheirandish, Keiji Ueshima, Atsushi Hashimoto, Takashi Ishida,
Hideaki Sugawara, Takahiro Yamamoto, Manabu Hisida, Shigeru Kuchiishi, Rika Yamada

Abstract
In this research, we develop a common fundamental aerodynamic analysis tool by extending FaSTARcode to be able to handle fluid-structure interaction problems aimed for establishing the technical basis
which accelerate the development of civil airplanes.
http://www.aero.jaxa.jp/eng/research/basic/application/

Reasons for using of JSS2
JSS is necessary to complete numerical simulations of unsteady phenomenon and understand it in shorttime span .

Achievements of the YearFor the bechmarking of our aeroelastic analysis code, we computed flutter boundaries on AGARD wing
(Fig.1). The

computed flutter boundaries (Fig.2) are close to the experimental data and NASA's

FUN3D results.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 AGARD wing

Fig.2 Comaprison of flutter boudaries

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

1024

Elapsed Time per Case

48.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.40
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

2,594,985.60

0.34

SORA-PP

107,058.28

1.34

SORA-LM495.880.26

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

326.23

0.23

/data

24,172.38

0.45

/ltmp

4,515.98

0.34

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

2.26

0.10

*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

Innovation for Design, Data-acquisition, Trouble-shoot and Certification in Aircraft
Development: Aerodynamic Optimization
Report Number：R17EA3202
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4395/
Responsible Representative
Takeshi Ito, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation HubCenterContact Information
Shigeru Kuchi-Ishi shigeruk@chofu.jaxa.jp

Members
Shigeru Kuchiishi, Takashi Ishida, Atsushi Hashimoto, Masahiro Kanazaki, Suzuki Kohji,
Takatoshi Nakayama, Minoru Yoshimoto, Shinsuke Nishimura, Yukinori Morita,
Takuya Ogura, Kazufumi Uwatoko

Abstract
An aerodynamic optimization tool using the unstructured CFD code FaSTAR is develped and its
validity and efficiency are examined. A Multi-Objective Evolutionary Algorithm (MOEA) is employed
as an aerodynamic optimization method. This tool is aimed to enable the direct evolutionary computing
to perform within a practical computational time by utilizing the high speed performance of FaSTAR. In
the present project, basic programs are developed and validated using JSS2.

Reasons for using of JSS2
Aerodynamic optimization using an evolutionary algorithm requires a number of high-fidelity andlarge-scaled computations (3D RANS analysis) and needs to use the supercomputer.

Achievements of the YearFor the Multi-Objective Evlutionary Algorithm (MOEA), the program was extended to the Nondominated Sorting Genetic Algorithms-II (NSGA-II) that enables to produce more equable anddiversified parate-optimal solutions. Also the directed mating algorithm was introduced to enhancerobustness of the program for problems including constraint conditions. The program was applied toa constrained optimization problem for the NASA Common Research Model (CRM) and it was foundJAXA Supercomputer System Annual Report April 2017-March 2018that the present program can produce optimal solutions more effectively compared to the foregoingprogram.

Fig.1 NASA CRM airfoil optimization result

Fig.2 Comparison of the optimal solution convergence history

Publications
 Presentations
1) Kanazaki, M., Kuchi-Ishi, S., and Suzuki K., ``Development of an Aerodynamic Optimization
Library by Evolutionary Algorithm,'' FaSTAR User's Conference, Akihabara Convention Hall,
2017.

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

96 - 512

Elapsed Time per Case

240.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.10
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA356,995.84

0.05

SORA-PP

55,829.90

0.70

SORA-LM

0.02

0.00

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

587.53

0.41

/data

24,481.17

0.45

/ltmp

8,646.34

0.65

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.32

0.01

*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

Innovation for Design, Data-acquisition, Trouble-shoot and Certification in Aircraft
Development: Basic Techniques for Real Flight Prediction
Report Number：R17EA3203
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4396/
Responsible Representative
Takeshi Ito,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Kazuyuki Nakakita nakakita@chofu.jaxa.jp

Members
Kazuyuki Nakakita, Shunsuke Koike, Shigeru Kuchiishi, Kanako Yasue, Hiroshi Kato,
Mitsuhiro Murayama, Kentaro Tanaka, Tohru Hirai, Yasushi Ito, Keita Hatanaka, Hiroya Toriida

Abstract
The Aerodynamic Prediction Technology, which is a part of the Innovation for Design, Dataacquisition, Trouble-shoot and Certification in Aircraft Development, constructs the assist technologies
to accelerate domestic aircraft development sequences using basic aerodynamic technologies. The targetof the Aerodynamic Prediction Technology is paradigm shift fromartisanal prediction to analytical one to accelerate domestic aircraft development sequences. This
research aims to develop a computational fluid dynamics (CFD) method for simulating the effect ofaerodynamic devices, such as vortex generators (VGs) and dorsal fins, to predict the aerodynamic
installation effect of the aerodynamic devices on real aircraft, and the developpment of data assimilation
method for turbulent transition flows.

Reasons for using of JSS2
Computational simulations using the JSS2 reveals detailed physical phenomena of the aerodynamic
devices, which is difficult only with wind tunnel tests, and development of the aerodynamic performance
prediction tools.

Achievements of the YearFor the research about aerodynamic improvement devices, computational fluid dynamics simulations
using the TAS code showed that vortices generated around retrofit aerodynamic improvement devices,such as vortex generators (VGs) and dorsal fins (DFs), interact with boundary layer on the vertical

JAXA Supercomputer System Annual Report April 2017-March 2018

stabilizer and its rudder, and improve their performance by reducing boundary layer separation shownin Fig. 1. Wind tunnel tests were also conducted to validate computational results. VGs improved theperformance of the vertical stabilizer slightly at low sideslip angles by reducing flow separation on therudder, and DFs greatly at high sideslip angles by strong vortices generated around them.
For the research about data assimulation, sensitivity analysis of observation type was employed by using
the developed data assimilation method for turbulent transition flows shown in Fig. 2. As a result, it wasclarified that the leading edge temperature information has similar sensitivity to the estimation of the
turbulent transition flow to the information of the velocity profile in theboundary layer.

Fig.1 Total pressure isosurface colored by wall distance for the baseline dorsal fineconfiguration with 11 VGs at mid-chord (Reynolds number of 0.52 million and rudderdeflection angle of 20degrees)JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.2 Sensitivity analysis result of observation type for the turbulent transition flow

Publications
 Non peer-reviewed papers
1) Ito, Y., Murayama, M., Koike, S., Yamamoto, K., Nakakita, K. and Kusunose, K., "Computational
Investigation of Vertical Stabilizer with Vortex Generators and Dorsal Fin," 36th AIAA Applied
Aerodynamics Conference, Atlanta, GA, 2018, to be presented.

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

64 - 256

Elapsed Time per Case

15.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.32
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

11,119,009.13

1.47

SORA-PP

1,752.79

0.02

SORA-LM

39.62

0.02

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

044.28

0.03

/data

9,015.23

0.17

/ltmp

5,574.70

0.42

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

4.57

0.20

*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 coupled analysis of motion and aerodynamics
Report Number：R17EA3210
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4397/
Responsible Representative
Takeshi Ito, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation HubCenterContact Information
Takashi Ishida ishida.takashi@jaxa.jp

Members
Atsushi Hashimoto, Takashi Ishida, Hideaki Sugawara, Keiji Ueshima, Minoru Yoshimoto,
Takuya Ogura, Shinsuke Nishimura, Yukinori Morita, Kazuhiro Imai, Shigeru Kuchiishi

Abstract
In this research, we have extended FaSTAR-code to be able to handle coupled analysis of motion andaerodynamics and conducted a store-separation analysis for the validation.

Reasons for using of JSS2
Computer for large-scale unsteady flow simulation

Achievements of the YearIn this year, we have reduced the memory cost and accelerated the computational speed of FaSTARMove to enhance the user's convenience. As a result, the unsteady flow simulation of store-separation
analysis with 10M grid points was finished within one-day.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Computational grid of store-separation analysis

Fig.2 Comparison of the memory performanceJAXA Supercomputer System Annual Report April 2017-March 2018

Publications
 Presentations
1) Keiji Ueshima, et al., "Development of FaSTAR-Move for flow analysis around moving/deforming
bodies", 49th Fluid Dynamics Conference/35nd Aerospace Numerical Simulation Symposium,
Tokyo, 20172) Keiji Ueshima, et al., "Improvement of FaSTAR-Move capability towards practical use", 55th
Aircraft Symposium, Shimane, 2017

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

64 - 2048

Elapsed Time per Case

20.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.45
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

11,678,000.75

1.54

SORA-PP

61,313.68

0.77

SORA-LM

12,511.32

6.44

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

121.34

0.08

/data

23,151.11

0.43

/ltmp

4,072.77

0.31

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.52

0.02

*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

Collaborative work for aerodynamic optimization
Report Number：R17EA3211
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4398/
Responsible Representative
Takeshi Ito, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation HubCenterContact Information
Shigeru Kuchi-Ishi shigeruk@chofu.jaxa.jp

Members
Shigeru Kuchiishi, Minoru Yoshimoto, Shinsuke Nishimura, Yukinori Morita, Takuya Ogura

Abstract
An aerodynamic optimization tool by using the unstructured CFD code FaSTAR is developed. As acollaborative work with an airfcraft industory, an overset grid function of FaSTAR-Move, a CFD tool formoving/deforming body analysis, is applied to an optimal arrangement of slat/flap for a threedimensional high lift device configuration.

Reasons for using of JSS2
Aerodynamic optimization using an evolutionary algorithm requires a number of high-fidelity andlarge-scaled computations (3D RANS analysis) and the use of a supercomputer is necessary.

Achievements of the Year
By setting an optimization problem for the slat arrangement of a three-dimensional high lift device
configuration, an optimization calculation using the overset grid function of FSTAR-Move together
with the response surface methodology was carried out. It was confirmed that the efficiency of the aircraft
configuration design process can be improved not only by the reduction of grid generation time
employing overset grid system, but also by the reduction of domain partition process for parallel
computations.

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.1 Optimization for the slat arrangement of a three-dimensional high lift device.

Fig.2 Example of the overset grid around a slat.

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

1600

Elapsed Time per Case

6.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.01
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

15,086.58

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

015.69

0.01

/data

10,503.48

0.19

/ltmp

3,210.14

0.24

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

0.26

0.01

*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

Study of the Aerodynamic Interaction between the rotor
and the wing on a compound helicopter
Report Number：R17EA3301
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4399/
Responsible Representative
Yasutada Tanabe, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation
Hub Center

Contact Information
Yasutada Tanabe tanabe.yasutada@jaxa.jp

Members
Masahiko Sugiura, Yasutada Tanabe, Hideaki Sugawara, Ryo Hayakawa

Abstract
A distinctive concept of compound helicopter is proposed by JAXA. Several key technologies have beenrecognized and investigated so far. Within them, the aerodynamic interaction between the main rotor
and the wing may cause remarkable increase of the aerodynamic drag of the aircraft. With functional
extensions of a CFD code for rotorcraft, rFlow3D, the interaction is simulated under same lift condition
during high speed flight. Designs of optimal low drag wing and rotor are the final goals of this research.
http://www.aero.jaxa.jp/eng/research/frontier/rotary/

Reasons for using of JSS2
The flowfield around a compound helicopter is very complicated because of the existence of multiple
rotors and complex fuselage. It is required to assign a large amount of computational grid points aroundthe aircraft. Also with the rotating blades, the flowfield is intrinsically unsteady and need a long time of
CPU hours. The JSS2 supercomputer with abundant computing resources is absolutely neccessary forthis research.

Achievements of the Year
Referred to the geometry of the main rotor blade of an existing helicopter, UH-60A, where publishedwind tunnel testing data are available, a rectangular fixed wing is placed under the rotor. At high advance
ratio flight, due to the aerodynamic interaction between the main rotor and the wing, the aerodynamic
drag of the combined rotor and wing increased about 20% compared to the combination of an isolated

JAXA Supercomputer System Annual Report April 2017-March 2018

rotor and an isolated wing with same lift. A sample of the flowfield around a full configuration compound
helicopter is shown in Figure 1. The flowfield on the advancing side and on the retreating side of therotor is shown in Figure 2 illustrating the interaction between a rotor and a wing.

Fig.1 A sample of the flowfield around a full configuration compound helicopter

Fig.2 Rotor/Wing interaction flowfield on the advancing side and on the retreating

JAXA Supercomputer System Annual Report April 2017-March 2018

side of the rotor
Publications
 Peer-reviewed papers
1) Atthaphon Ariyarit, Masahiko Sugiura, Tanabe Yasutada, Masahiro Kanazaki, "Hybrid surrogatemodel-based multi-fidelity efficient global optimization applied to helicopter blade design,"
Engineering Optimization, Taylor & Francis, pp. 1-25, Sept. 2017.
 Non peer-reviewed papers
1) Masahiko Sugiura , Yasutada Tanabe , Hideaki Sugawara, George N. Barakos , Naoki Matayoshi ,Hirokazu Ishii, " Validation of CFD Codes for the Helicopter Wake in Ground Effect," 43rd
European Rotorcraft Forum, Sep. 13, 2017, Milano, Italy.
2) Masahiko Sugiura, Yasutada Tanabe, Hideaki Sugawara, "Optimal Aerodynamic Design of Main
Rotor Blade for a High-Speed Compound Helicopter," 6th Asian-Australian Rotorcraft Forum &Heli Japan 2017, November 7-9, 2017, Kanazawa, Japan.
3) Hideaki Sugawara, Yasutada Tanabe, "A Study of Rotor/Wing Aerodynamic Interaction at High
Speed Flight on a Compound Helicopter," 6th Asian-Australian Rotorcraft Forum & Heli Japan 2017,
November 7-9, 2017, Kanazawa, Japan.
4) Gunther Wilke, Annika Moller-Langer, Yasutada Tanabe, Masahiko Sugiura, Hideaki Sugawara,"Tackling the HARTII test case: A joint effort by DLR and JAXA," 6th Asian-Australian Rotorcraft
Forum & Heli Japan 2017, November 7-9, 2017, Kanazawa, Japan.
5) Koichi Yonezawa, Tomoki Kagayama, Shigeru Sunada, Kazuyasu Sugiyama, Noboru Kobiki,
Yasutada Tanabe, Masahiko Sugiura, Takashi Aoyama, " An Experimental Study of Aerodynamics
of a Compound Helicopter," 6th Asian-Australian Rotorcraft Forum & Heli Japan 2017, November
7-9, 2017, Kanazawa, Japan.
6) Yusuke Hamamoto, Takeshi Akasaka, Yasutada Tanabe, "Experimental Investigation of the RotorWing Aerodynamic Interaction on a Compound Helicopter in High Advance Ratio," 6th AsianAustralian Rotorcraft Forum & Heli Japan 2017, November 7-9, 2017, Kanazawa, Japan.
7) Keiichiro Makino, Takeshi Akasaka, Yusuke Hamamoto, Masatoshi Inaba, Yasutada Tanabe,"Experimental Investigation of the Rotor-Wing Aerodynamic Interaction on a Compound
Helicopter in Hover," 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

360.00 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

2,566,629.41

0.34

SORA-PP

215,684.86

2.70

SORA-LM

0.00

0.00

SORA-TPP

3,579.92

0.40

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

271.40

0.19

/data

17,050.12

0.32

/ltmp

3,011.07

0.23

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

Studies on real flight aerodynamic prediction
Report Number：R17EA3602
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4400/
Responsible Representative
Takeshi Ito, Aeronautical Technology Directorate, Next Generation Aeronautical Innovation HubCenterContact Information
Kazuyuki Nakakita nakakita@chofu.jaxa.jp

Members
Keiko Kawaguchi, Kazuyuki Nakakita, Kanako Yasue, Rie Tagai, Makoto Ueno,
Mitsuhiro Murayama, Kentaro Tanaka, Tohru Hirai, Yasushi Ito, Keita Hatanaka,
Suzuki Kohji, Takahiro Uchiyama, Hiroya Toriida, Shu Yamagishi

Abstract
Through a series of aerodynamic design sequence in the aircraft development, we aim to speed up thatsequence by cutting-edge technologies which enable us to avoid from the delay of the development andspeed-up the aerodynamic sequence.
By applying the sophisticated data analysis techniques to high-speed buffet data produced by unsteady
CFD, a technology to detecting the sign and location of buffet phenomena is developped. An analysis to
replicate Reyunolds number effect appeared on aerodynamic characteristics is also conducted to develop
the future real flight aerodynamic prediction .

Reasons for using of JSS2
A huge parallel computar like JSS2 is required to carry out large-scale analysis for unsteady buffet
phenomena and high precision computations for evaluating the Reynolds number effect.

Achievements of the YearFor the research of beffet onset detection, unsteady CFD calculation introducing DES was applied to
2-dimensinal NACA0012 airfoil at M=0.72 and AOA=3 to 6 degree. (Fig. 1) The buffet onset was
detected from the unsteady CFD results by the conventional method using CLrms.

(Fig. 2) The

unsteady CFD results was also used for the develpment of new buffet onset detection techniques using
data-mining methods.
The Reynolds number research was conducted using the airfoil of the C-141 aircraft, which was

JAXA Supercomputer System Annual Report April 2017-March 2018

occurred a problem due to Reynolds number effect. The Reynolds number effect of C-141 airfoil was
evaluated in wide range of Reynolds number variations. (Fig.3)

Fig.1 Pressure distribution including shock-wave location on a NACA0012 airfoil at
M=0.72 and AoA=3deg.

Fig.2 Detection of the starting point of buffet phenomen using CLrms from unsteady CFD results

JAXA Supercomputer System Annual Report April 2017-March 2018

Fig.3 Pressure distribution around a quasi 2-dimensional C-141 airfoil employing
transition model for turbulence modeling.

Publications
 Peer-reviewed papers
1) Yamazaki, W., Yamagishi, S., and Ueno, M,. "Investigation of Indirect Reynolds Number Effectvia Computational Fluid Dynamics Simulations", Journal of Aircraft, Posted online on 30 Jan 2018.
 Non peer-reviewed papers
1) Kazuhisa Chiba, Yuhei Umeda, Naoki Hamada, Shinya Watanabe, Masaya Nakata, Kanako Yasue,
Koji Suzuki, Takashi Atobe, Shigeru Kuchi-Ishi, Kazuyuki Nakakita, Takeshi Ito, Determination of
Temporal and Spatial Origination of Transonic Buffet via Unsteady Data Mining, AIAA 2018-0036,
2018 AIAA Aerospace Sciences Meeting, 2018.
2) Yamazaki, W, Yamagishi, W and Ueno, M., "Investigation of Indirect Reynolds Number Effect via
Computational Fluid Dynamics Simulations," 35th AIAA Applied Aerodynamics Conference, AIAA
2017-3404, 2017.
3) Yamazaki, W, Yamagishi, W and Ueno, M., "Investigation of Indirect Reynolds Number Effect of
C-141 Aircraft Model," Proceedings of the Fourteenth International Conference on Fluid Dynamics,
2017.

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

128 - 512

Elapsed Time per Case

720.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 1.92
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

15,973,279.51

2.13

SORA-PP

12,985.28

0.16

SORA-LM

313.000.16

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

130.33

0.09

/data

25,241.03

0.47

/ltmp

8,191.38

0.62

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

5.27

0.23

*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 and development for system integration of silent supersonic airplane
technologies
Report Number：R17EA3800
Subject Category：Aeronautical Technology
URL：https://www.jss.jaxa.jp/ar/e2017/4401/
Responsible Representative
Yoshikazu Makino,
Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center

Contact Information
Yoshikazu Makino makino.yoshikazu@jaxa.jp

Members
Junichi Akatsuka, Naoko Tokugawa, Hiroaki Ishikawa, Yoshine Ueda, Dongyoun Kwak,
Keisuke Ohira, Atsushi Ueno, Satoshi Kondo, Tatsunori Yuhara

Abstract
Currently, airplanes fly at about Mach 0.8, which is markedly slower than the speed of sound. FromJapan, which is distant from Europe and the United States, it takes more than 12 hours to fly the distance.
If we were able to fly faster than the speed of sound, for example at twice the speed, then the time forflying would be halved and the flight duration from Japan to Europe or the United States would be about
6 hours. If the travelling time were shortened, then economic activities would be bolstered by increased
opportunities for business and tourism. Moreover, measures against natural disasters could be taken
quickly, thereby ushering in a safer and more affluent society. If the flight duration were less than 6 hours,
then the increasing frequency of hazards, nuisances, and ailments such as economy-class syndrome could
be prevented. Perhaps most importantly, everyone would be able to enjoy travel more comfortably thanever. These airplanes that enable high-speed transportation, which fly at a speed faster than the speedof sound, are called supersonic civil transport.
Although the realization of supersonic civil transport is highly anticipated, successors to the Concorde,which was retired in 2003, have not been forthcoming. Shortcomings of the Concorde included poor fuelconsumption and extremely high operational costs. In addition, because sonic booms are created,supersonic flight over land was not permitted. Its routes were severely restricted, which is another reason
that business success eluded the Concorde. During flight experiments in 2005, using NEXST-1, a small
supersonic experimental plane, JAXA demonstrated a technology to reduce air resistance and to improvefuel consumption efficiency. The D-SEND project first phase test was conducted in 2011. The second
phase test was conducted in 2015, in an attempt to verify the concept of an airframe design technology
for sonic boom abatement. As described, key technologies will be acquired to meet the requirements of

JAXA Supercomputer System Annual Report April 2017-March 2018supersonic passenger aircraft and to present JAXA's original low sonic boom design concept model,"Quieter supersonic civil transport".
http://www.aero.jaxa.jp/eng/research/frontier/sst/

Reasons for using of JSS2
In the R&D for system integration of silent supersonic airplane technologies, the airplane design studyof a small-size civil supersonic transport is conducted. Simulations for evaluating the aerodynamic
performance and noise characteristics are conducted using JAXA supercomputer system.

Achievements of the YearA parametric design study of wing planform is conducted in order to improve both cruise performanceand low-speed performance of our supersonic concept.

Fig.1 Wing planforms

Publications
N/A

JAXA Supercomputer System Annual Report April 2017-March 2018

Usage of JSS2
 Computational Information
Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelizatio

Number of Processes

300

Elapsed Time per Case

1.00 hours

 Resources Used
Fraction of Usage in Total Resources*1 (%): 0.89
Details
Computing Resources
System Name

Amount of Core Time (core x hours)

Fraction of Usage*2 (%)

SORA-MA

5,616,847.60

0.74

SORA-PP

315,231.36

3.95

SORA-LM

5,570.59

2.87

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage assigned(GiB)

Fraction of Usage*2 (%)/home

366.40

0.25

/data

12,584.53

0.23

/ltmp

8,203.13

0.62

Archiver Resources
Archiver System Name

Storage used(TiB)

Fraction of Usage*2 (%)

J-SPACE

3.05

0.13

*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