JAXA Supercomputer System Annual Report April 2017-March 2018

Report Number: R17EA2121

Subject Category: Aeronautical Technology

PDF available here

• Responsible Representative: Takashi Yamane, Aeronautical Technology Directorate, Propulsion Research Unit
• Contact Information: Hideyuki Taguchi taguchi.hideyuki@jaxa.jp
• Members: Hideyuki Taguchi, Motoyuki Hongoh, Masaharu Hiruma, Jun Butsuen, Masahiro Uji, Yuki Kayama

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

Please refer to 'Hypersonic passenger aircraft technology | Sky Frontier – Sky Frontier Program | Aeronautical Technology Directorate'.

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

(1) Aerodynamics of the Hypersonic Cruise Experimental Aircraft was evaluated by CFD analyses. (Fig.1)

(2) Aerodynamics of the High Mach Integreted Control Experimental Aircraft was evaluated by CFD analyses. (Fig.2, Fig. 3)

Fig.1: Hypersonic Cruise Experimental Aircraft (Cp Contour, Mach 7, AoA=0deg)

Fig.2: Hypersonic Control Experimental Aircraft (Cp Contour, Mach 5, AoA=15deg)

Fig.3: High Mach Integrated Control Experimental Aircraft (Mach Contour, Mach 5, AoA=0deg)

Publications

■ Non peer-reviewed papers

1) Hiruma, M., Hirotani, T., Hongoh, M., Taguchi, T. and Tezuka, A., "Aerodynamic Evaluation of Hypersonic Cruise Experimental Aircraft," 61th Joint Conference on Space Science and Technology, 2017.

2) Butsuen, J., Hirotani, T., Taguchi, T., Hongoh, M., Tezuka, A. and Hiruma, M, "Lateral and Directional Aerodynamics Evaluation of High Mach Integrated Control Experimental Aircraft," 55th Aircraft Symposium, 2017.

■ Presentations

1) Hiruma, M., Hirotani, T., Hongoh, M., Taguchi, T. and Tezuka, A., "Aerodynamic Evaluation of Hypersonic Cruise Experimental Aircraft," 61th Joint Conference on Space Science and Technology, 2017.

2) Butsuen, J., Hirotani, T., Taguchi, T., Hongoh, M., Tezuka, A. and Hiruma, M, "Lateral and Directional Aerodynamics Evaluation of High Mach Integrated Control Experimental Aircraft," 55th Aircraft Symposium, 2017.

Usage of JSS2

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 60 - 144
• Elapsed Time per Case: 72.00 hours

Resources Used

Fraction of Usage in Total Resources*1(%): 0.84

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 2017-March 2018