JAXA Special Publication JAXA-SP-19-003E

Numerical Study on Combustible Flow in Supersonic Flight Engines and Rocket Engines
Report Number: R18EACA01
Subject Category: JSS2 Inter-University Research
URL: https://www.jss.jaxa.jp/en/ar/e2018/9088/
Responsible Representative
Nobuyuki Tsuboi, Professor, Department of Mechanical and Control Engineering, Kyushu Institute ofTechnology
Contact Information
Nobuyuki Tsuboi (tsuboi@mech.kyutech.ac.jp)
Members
Toshihiro Iwasa, Takahide Araki, Nobuyuki Tsuboi, Yoshiki Nishikawa, Tomoki Uzaki, Ryuji Takahashi, AyuAgou, Kouhei Ozawa, Nicolas H. Jourdaine, Shota Goto, Kodai Shimomura, Kenta Murayama, Takuro Yoshino,
Tomohiro Watanabe
Abstract
Fundamental studies on nozzles and combustors for Japanese rocket engines and supersonic engines are
performed by using numerical simulations.
Ref. URL: http://www.mech.kyutech.ac.jp/rfd/eng-theme.html
Reasons for using JSS2
Academic and applicative researches on fluid dynamics and combustion mechanism, and development ofeffective numerical methods are carried out in order to develop Japanese rocket engines and supersonic engines.
Achievements of the Year
Three-dimensional numerical simulations on a slit-shaped hydrogen jet under high momentum flux ratio insupersonic freestream are performed to evaluate the jet mixing. The results show that the jet penetration is highand hydrogen is transported in a span-wise direction and is distributed widely, as shown in Fig. 1. Multiple
longitudinal vortices around the jet entrain the hydrogen jet and mix with the freestream, as shown in Fig. 2. In
this mixing process, key parameters are jet trajectory and the strength of the vortex. These parameters strongly
depend on the momentum flux ratio and pressure ratio.

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JAXA Supercomputer System Annual Report (April 2018-March 2019)

Fig. 1: Time-averaged hydrogen mass fraction contours.

Fig. 2: Q value (50) isosurface contours. Color means velocity magnitude.

Publications- Oral Presentations[1] Toshihiro Iwasa, Keiichiro Fujimoto, Daiki Muto, Nobuyuki Tsuboi, Numerical Simulations of Hydrogen
Jet Mixing in Supersonic Crossflow for Liquid Rocket Commanded Destruction, 12th Asian Computational Fluid
Dynamics Conference, 0104, Yilan, Taiwan, October, 2018.
[2] Yoshiki Nishikawa, Nobuyuki Tsuboi, Takashi Ito, Satoshi Nonaka, Numerical Study on Aerodynamic
Characteristics of Reusable Vehicle-eXperiment Rocket with Body-flap during Gliding, 15th International
Conference on Flow Dynamics, GS1-30, Sendai, Japan, November, 2018.

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JAXA Special Publication JAXA-SP-19-003E

Usage of JSS2


Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

8 - 12Elapsed Time per Case

141 Hour (s)Resources Used
Fraction of Usage in Total Resources*1 (%): 0.12
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

1,012,583.98

0.12

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

123.98

0.13

/data

1,239.78

0.02

/ltmp

25,390.64

2.17Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
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.

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