JAXA Supercomputer System Annual Report April 2020-March 2021

Report Number: R20EU0902

Subject Category: Space and Astronautical Science

PDF available here

• Responsible Representative: Akira Oyama, Associate Professor, Institute of Space and Astronautical Science, JAXA
• Contact Information: Akira Oyama(oyama@flab.isas.jaxa.jp)
• Members: Akira Oyama, Shigetaka Kawai, Satoshi Sekimoto, Daiki Terakado, Satoshi Shimomura, Taku Nonomura, Shota Taniguchi, Bimo Dwianto, Takuma Saito, Naruhiko Nimura, Kento Kaneko, Yuuki Fukushima, Motoki Sato

Abstract

We conduct fundamental research on aerodynamics such as aerodynamic design of Mars aircraft.

Reference URL

Please refer to 'Akira Oyama Laboratory of Aerodynamics and Design in Space Engineering'.

Reasons and benefits of using JAXA Supercomputer System

Large eddy simulation is required for analysis of Mars airplane .

Achievements of the Year

Numerical analysis to design electric aircraft considering interaction between propeller and main wing. All simulations are conducted by FaSTAR move, which is developed by JAXA. We conducted numerical simulation of main wing, nacelle and propeller. The effect of propeller mounting position is investigated. An example of the results are shown in Fig.1. Numerical results and wind tunnel experiments show agreements for flow field features such as suppression of separation due to propeller wake and main wing surface flow. Both results also show agreement for the aerodynamic characteristic coefficients.

As for Mars airplane design, aerodynamic performance evaluation of optimized airfoil with external rib structure using LES. Under its cruise condition, the external ribs don't inhibit the formation of votices on suction side and therefore don't degredate the aerodynamic performance. Also, it is implied that the rib strucure promotes the reattachment of the separated flow at high angle of attack. These findings indicate that the optimized airfoil with external rib structure is useful as the main wing of Mars airplane.

Fig.1: Main wing's surface streamline and iso surface of Q ctriterion

Fig.2: Visualization of velocity field with vortices (top) and vortices on suction side(bottom). (Left: with external rib structure, Right: without rib structure)

Publications

- Peer-reviewed papers

Shigetaka Kawai and Akira Oyama, Uncertainty Quantification and Global Sensitivity Analysis of Low-Reynolds-Number Airfoil for Future Mars Airplane, Transactions of the Japan society for aeronautical and space sciences, Vol. 63, No. 4, pp. 172-184, 2020.

- Oral Presentations

Naruhiko Nimura, Shun Tamura, and Akira Oyama, High Angle-of-Attack Aerodynamic Characteristics of Thin-Trailing-Edge Airfoil with External Ribs, AIAA SCITECH, Virtual Event, 11-15 January 2021.

Shigetaka Kawai, Wataru Yamazaki, Akira Oyama, Uncertainty Quantification of Supersonic Biplane Airfoil by Multi-Element Polynomial Chaos Based on Edge, AIAA SCITECH, Virtual Event, 11-15 January 2021.

Usage of JSS

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 12 - 37
• Elapsed Time per Case: 350 Hour(s)

Resources Used(JSS2)

Fraction of Usage in Total Resources*1(%): 1.25

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.

Resources Used(JSS3)

Fraction of Usage in Total Resources*1(%): 1.20

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.

JAXA Supercomputer System Annual Report April 2020-March 2021