JAXA Supercomputer System Annual Report April 2018-March 2019

Report Number: R18EA2121

Subject Category: Aeronautical Technology

PDF available here

• 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 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 for using JSS2

We need a long calcularion time to obtaine the aerodynamic characteristics of the overall hypersonic experimental 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, Fig3, Fig4)

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)

Fig.4: High Mach Integrated Control Experiment(HIMICO) Vehicle with 15deg of elevator angle(HIMICO 2, Mach Contour and Streamline, Vertical Three-Component 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 Information

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

Resources Used

Fraction of Usage in Total Resources*1(%): 0.77

Details

Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.

*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 2018-March 2019