JAXA Supercomputer System Annual Report February 2021-January 2022

Report Number: R21EA2121

Subject Category: Aeronautical Technology

PDF available here

• Responsible Representative: Sadatake Tomioka, Leader, Hydrogen Aerospace Plane Team
• Contact Information: Hideyuki Taguchi(taguchi.hideyuki@jaxa.jp)
• Members: Manami Fujii, Mizuki Fukazawa, Motoyuki Hongoh, Yusuke Hoshiya, Daiki Ito, Yuki Kuwabara, Masafumi Momose, Koichi Omi, Junichi Oki, Takahiro Terao, Nozomi Takaki, Rintaro Tanaka, Hideyuki Taguchi, Kotaro Yamada, Kotaro Yoshihara, Kazutaka Yamada

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 hypersonic engines. 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 pre-cooled turbojet engine.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

We need a long calcularion time to obtaine the aerodynamic characteristics of the overall hypersonic experimental aircraft by CFD analyses.

Achievements of the Year

LES of combustion inside the model afterburner of pre-cooled turbojet engine with single injector. Two case of different injection hole diameter(1.0 mm and 1.4 mm) at equivalence ratio of 2.3 were conducted.

The aerodynamic characteristic of low-speed experimental aircraft with engine nacels on the main wings and with landing gears and a pulse detnation engine under the body was evaluaetd by CFD.

Fig.1: moler fraction of H2,O2, H20, equivalence ratio and temperature distribution at the plane including 60 deg injection hole.

Fig.2: Low-Speed Experimental Aircraft (Pressure Coefficient Contour, Mach 0.147, AoA: 0deg)

Fig.3: Low-Speed Experimental Aircraft (Longitudinal Three Component Force Compared With Wind Tunnel Test, Mach 0.147)

Publications

- Non peer-reviewed papers

Mizuki Fukazawa, Tomonari Hirotani, Hideyuki Taguchi, Kazumasa Kamisori, Asei Tezuka, Evaluation of effect on model support method in a low speed wind tunnel test of double delta wing aircraft with engines, 59th Aircraft Symposium, 2021.

- Oral Presentations

Mizuki Fukazawa, Tomonari Hirotani, Hideyuki Taguchi, Kazumasa Kamisori, Asei Tezuka, Evaluation of effect on model support method in a low speed wind tunnel test of double delta wing aircraft with engines, 59th Aircraft Symposium, 2021.

Usage of JSS

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 1 - 2
• Elapsed Time per Case: 30 Hour(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 1.03

Details

Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.

*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.

ISV Software Licenses Used

*2: Fraction of Usage：Percentage of usage relative to each resource used in one year.

JAXA Supercomputer System Annual Report February 2021-January 2022