JAXA Supercomputer System Annual Report February 2025-January 2026

Report Number: R25EACA59

Subject Category: JSS Inter-University Research

PDF (to be added)

• Responsible Representative: Masahiro Kanazaki, Professor, Tokyo Metopolitan University
• Contact Information: Masahiro Kanazaki, Professor(kana@tmu.ac.jp)
• Members: Masahiro Kanazaki, Hikari Kono, Takashi Matsuno, Taisei Takagi, Yoshiharu Tamaki, Mana Yokoi

Abstract

In this study, we devised rotor blades using thin cambered airfoils as a concept for storing a Mars exploration helicopter in a size and shape suitable for transportation by rocket. We performed numerical simulations and optimal design from the perspectives of aerodynamics, propulsion, and uncertainties related to structural deformation caused by the thin airfoils.

In the optimal design phase, we used momentum theory based on two-dimensional airfoil evaluation and conducted a global search using evolutionary computation. As a result, we obtained an airfoil that demonstrated excellent average performance and robustness compared to NASA’s Mars helicopter.

We also carried out structural evaluations regarding concerns about structural strength due to the thin airfoil configuration and confirmed that the safety factor is maintained.

Reference URL

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Reasons and benefits of using JAXA Supercomputer System

In this study, we conduct optimal design using a global optimization method. Since the design targets the cross-sectional airfoil shape, a two-dimensional airfoil analysis is required for each design candidate within the blade element momentum theory. Although the use of a low‑cost evaluation method enables the application of evolutionary computation, performing both computational fluid dynamics and structural evaluations makes the use of JSS3 indispensable. For verification simulations using numerical methods based on overset grids, the computational capability of JSS3 is also required.

Achievements of the Year

In this study, we carried out an airfoil optimization for blades that employ thin cambered airfoils, taking into account uncertainties related to aerodynamics, propulsion, and structural deformation resulting from the thin airfoil geometry. The optimization incorporated evolutionary computation together with uncertainty quantification using Polynomial Chaos. As a result, as shown in Fig. 1, a blade planform with excellent aerodynamic performance was obtained. This design was then evaluated through load calculations (Fig. 2), confirming that failures such as breakage would not occur.

Fig.1: Thrust coefficient–FoM diagram of the obtained airfoil

Fig.2: Results of the load calculation

Publications

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Usage of JSS

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 32
• Elapsed Time per Case: 2 Hour(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 0.14

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