JAXA Special Publication JAXA-SP-19-003E

Numerical Analyses on Hypersonic Experimental Aircraft
Report Number: R18EA2121
Subject Category: Aeronautical Technology
URL: https://www.jss.jaxa.jp/en/ar/e2018/9072/
Responsible Representative
Hideyuki Taguchi, Research Plan Manager, Propulsion Technology Research Unit, Aeronautical Technology
Directorate
Contact Information
Hideyuki Taguchi (taguchi.hideyuki@jaxa.jp)
Members
Motoyuki Hongoh, Masaharu Hiruma, Hideyuki Taguchi, Masahiro Uji, Yuki Kayama, Hiroyuki Tanaka
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 of hypersonic airframe and hypersonicengines. In addition to defining the required specifications of hypersonic aircraft, we present the design
specifications of the hypersonic experimental aircraft for carrying out flight demonstration of hypersonic precooled turbojet engine.
Reasons for using JSS2
We need a long calcularion time to obtaine the aerodynamic characteristics of the overall hypersonicexperimental aircraft by CFD analyses.
Achievements of the Year
Aerodynamic performances of the High Mach Integrated Control Experimental Aircraft (HIMICO) was
evaluated by CFD analyses. (Fig. 1, Fig. 2, Fig. 3, Fig. 4)－86－This document is provided by JAXA.

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

Fig. 1: High Mach Integrated Control Experiment (HIMICO) Vehicle (HIMICO 1,Mach Contour, Mach5, AoA = 0deg)

Fig. 2: High Mach Integrated Control Experiment (HIMICO) Vehicle with 15deg of
elevator angle (HIMICO 2, Cp Countour, Mach5, AoA = -15deg)

Fig. 3: High Mach Integrated Control Experiment (HIMICO) Vehicle with 15deg of
elevator angle (HIMICO 2, Streamline, Mach5, AoA = -15deg)－87－

This document is provided by JAXA.

JAXA Special Publication JAXA-SP-19-003E

Fig. 4: High Mach Integrated Control Experiment (HIMICO) Vehicle with 15deg of
elevator angle (HIMICO 2, Mach Contour and Streamline, Vertical ThreeComponent Force Compared with Wind Tunnel Test, Mach5)

Publications- Non peer-reviewed papers
1) Uji, M., Taguchi, H., Hirotani, T., Hongoh, M., Tezuka, A., “Evaluation of Flow Field around Flight Control
Surfaces of High-Mach Integrated Control Experiment (HIMICO) Vehicle,” 56th Aircraft Symposium, 2018.
- Oral Presentations
1) Uji, M., Taguchi, H., Hirotani, T., Hongoh, M., Tezuka, A., “Evaluation of Flow Field around Flight Control
Surfaces of High-Mach Integrated Control Experiment (HIMICO) Vehicle,” 56th Aircraft Symposium, 2018.

Usage of JSS2
Computational InformationProcess Parallelization Methods

MPI

Thread Parallelization Methods

OpenMP

Number of Processes

1-2

Elapsed Time per Case

30 Hour (s)－88－This document is provided by JAXA.

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

Resources Used
Fraction of Usage in Total Resources*1 (%): 0.77
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

6,703,794.51

0.82

SORA-PP

4,121.21

0.03

SORA-LM

3,514.47

1.64

SORA-TPP

0.00

0.00

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)/home

2,145.77

2.22/data

63,476.59

1.12/ltmp

8,789.07

0.75

Archiver 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.

－89－

This document is provided by JAXA.