JAXA Supercomputer System Annual Report February 2025-January 2026

Report Number: R25ECWU06

Subject Category: Cooperative Graduate School System

PDF (to be added)

• Responsible Representative: Yuichiro Aoki, Manager, Management and Integration Department
• Contact Information: Yuichiro Aoki(aoki.yuichiro@jaxa.jp)
• Members: Yuichiro Aoki, Yusuke Komeda, Yusuke Onozeki, Shunpei Shimizu

Abstract

Hypersonic vehicles offer great potential for future transport but require high aerodynamic performance and lightweight structures for efficiency and safety. This study proposes a hypersonic aircraft with a morphing wing to optimize performance from takeoff to hypersonic cruise. Using CFD, Newtonian analysis, and wind tunnel experiments, the aerodynamic behavior was evaluated. Additionally, quasi-static load analyses were performed to develop a lightweight, high-stiffness wing structure. Results show this design outperforms conventional hypersonic vehicles in both low-speed and hypersonic regimes.

Reference URL

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Reasons and benefits of using JAXA Supercomputer System

To investigate a hypersonic passenger aircraft aimed at high aerodynamic efficiency in both low-speed and hypersonic regimes, it is essential to visualize the flow field around the vehicle and understand the underlying phenomena through a comparison of wind tunnel experiments and CFD. Furthermore, leveraging the parallel computing capabilities of supercomputers is necessary to reduce the time required for the extensive number of CFD analysis cases.

Achievements of the Year

Fundamental engineering insights into the aerodynamic and structural design of hypersonic passenger aircraft were obtained through the following points:

1. Proposed an initial shape concept for a hypersonic aircraft featuring active, lightweight morphing wings prior to aerodynamic optimization.

2. Demonstrated, through both numerical analysis and wind tunnel testing, the potential for achieving high aerodynamic performance during both takeoff/landing and cruise phases.

3. Established design guidelines for the initial structural layout prior to topology optimization.

Fig.1: Aircraft Specifications

Fig.2: Aircraft Configuration

Fig.3: CFD at Hypersonic Cruise for Real Aircraft

Fig.4: Results –CFD vs Experiment at Hypersonic Cruise

Publications

- Oral Presentations

Y. Onozeki, S. Shimizu, B. Maximilien, Y. Aoki, Fundamental Study on Aerodynamic and Structural Analysis of Hypersonic Aircraft with Lightweight Morphing Wings during Takeoff, Landing, and Cruise, 63rd Aircraft Symposium, October 15-17, 2025.

Y. Onozeki, S. Shimizu, B. Maximilien, Y. Aoki, Combined Aerodynamic and Structural Study on Hypersonic Aircraft With Lightweight Morphing Wing From Takeoff to Cruise, AIAA SCITECH 2026 Forum, January, 2026

- Poster Presentations

Y. Onozeki, B. Maximilien, Y. Aoki, Hypersonic Aircraft with Variable-Sweep Morphing Wing: Concept and Experimental Evaluation for High Aerodynamic Performance, 69th Space Sciences and Technology Conference, November 25-28, 2025

Usage of JSS

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 2 - 36
• Elapsed Time per Case: 12 Hour(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 0.00

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 2025-January 2026