JAXA Special Publication JAXA-SP-19-003E

Basic research for system integration of silent supersonic airplane technologies
Report Number: R18ETET01
Subject Category: Skills Acquisition System
URL: https://www.jss.jaxa.jp/en/ar/e2018/9163/
Responsible Representative
Yoshikazu Makino, Aeronautical Technology Directorate, Aviation Systems Research Unit
Contact Information
Yoshikazu Makino (makino.yoshikazu@jaxa.jp)
Members
Yuki Kishi, Go Iwamoto, Masahiro Kanazaki, Yoshikazu Makino, Hideyuki Obata, Yuki Sato, Nao Setoguchi,Hidekazu Yoshida, Toshiya Yokoi
Abstract
The system integration design technologies for achieving low sonic-boom, low aerodynamic drag, low landing
and take-off noise, and light weight simultaneously are the key technologies for future supersonic airplanes. JAXA
is promoting the R&D for these technologies based on our experiences of demonstrating the advanced low-dragand low-boom design concepts.
Ref. URL: http://www.aero.jaxa.jp/eng/research/frontier/sst/
Reasons for using JSS2
To achieve low sonic-boom, low aerodynamic drag, low landing and take-off noise, and light weight
simultaneously, the multi-objective optimization tools are utilized in the design study. The super computer isnecessary to obtain the multiple objective function efficiently with many numerical simulations.
Achievements of the Year
Numerical analyses on exhaust nozzle shapes and jets for aft-boom shaping was conducted. The NASA nozzle
6 configuration was used as the baseline and effects of its inner profile, outer profile and nozzle pressure ratio on
the near field signature were investigated. It was found that the nozzle outer profile and the nozzle pressure ratio
are more sensitive to the near field signature than the nozzle inner profile. In addition, numerical simulations on
intake-buzz and an design study to seek an unconventional aircraft configuration to achieve higher sonic-boom
mitigation were performed using JSS2.

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This document is provided by JAXA.

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

Fig. 1: Schematic of numerical analysis and nozzle shapes

Fig. 2: Examples of near field signatures and flow fields

Publications- Oral Presentations
1) Obata, H., Akatsuka, J., Ueno, A., and Watanabe, Y., Numerical Investigation on Nozzle Exit Shape andPlume for Aft-Boom Mitigation of Supersonic Transport, Proceedings of The 59th Conference on Aerospace
Propulsion and Power (in Japanese)
2) Yoshida, H., Sato, Y., Murakami, K., Makino, Y., Ueno, A., Nakakita, K., Numerical Study using Detached
Edy Simulation (DES) of Supersonic Inlet Buzz for the Silent Supersonic Transport, Proceedings of the 56th
Aircraft Symposium (in Japanese)3) Kishi, Y., Makino, Y., Kanazaki, M., Aerodynamic Design of Low-boom SST by Forward-swept Wing
Consepti, Proceedings of the 56th Aircraft Symposium (in Japanese)－289－This document is provided by JAXA.

JAXA Special Publication JAXA-SP-19-003E

Usage of JSS2

Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelization

Number of Processes

30 - 120

Elapsed Time per Case

5 Hour (s)Resources Used
Fraction of Usage in Total Resources*1 (%): 1.16
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

9,439,538.43

1.16

SORA-PP

112,434.37

0.90

SORA-LM

6,185.91

2.88

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)/home

3,460.72

3.58

/data

105,100.96

1.85/ltmp

21,809.91

1.87

Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
1.78

0.06

*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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This document is provided by JAXA.