JAXA Supercomputer System Annual Report February 2021-January 2022

Report Number: R21ECWU07

Subject Category: Cooperative Graduate School System

PDF available here

• Responsible Representative: Sadatake Tomioka, Associate Pricipal Researcher, RInsertHereD Directorate, 4th Unit
• Contact Information: Sadatake Tomioka(tomioka.sadatake@jaxa.jp)
• Members: Shota Hatta, Naotaka Ikeda, Kota Kubosaki, Hironobu Nishiguchi, Sadatake Tomioka

Abstract

Research on future launch vehicle, namely a winged vehicle with air-breathing engines, with emphasis on propulsion system such as supersonic combustion ramjet, an activity of Tohoku Univ. - JAXA collabolative course.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

A high computational performance was required for high load computation such as 3D RANS/LES Hybrid CFD calculations, so that using JSS was necessary and helpful.

Achievements of the Year

Reacting flow field within a supersonic combustor was simulated using a RANS / LES hybrid method. By applying the hybrid method, both flow field (evaluated via pressure distribution, Fig. 1) and mixing phenomena (evaluated via fuel contour at the exit of the combustor, Fig. 2) were nicely simulated in comparison to the RANS method alone.

A method to mimic disturbance on the incoming flow to a combustor from the upstream inlet section was evaluated with CFD. Both flow fields within an engine model with inlet section and a direct-connect combustor with a shock wave generator were simulated with RANS method (Fig. 3), showing validity of the shock wave generator.

Fig.1: Comparison of wall pressure distributions, experimental, with RANS and with hybrid method

Fig.2: Comparison of fuel contours at exit of combustor, experimental, with RANS and with hybrid method

Fig.3: Comparison of pressure contours in cases with engine model and with direct-connect combsutor equipping shock wave generator.

Publications

- Non peer-reviewed papers

Nishiguchi, H., et al., 'Unsteady Numerical Analysis of a Dual-Mode Scramjet Combustor with Cavity,' ISTS paper 2022-a-10, 2022.

- Oral Presentations

Nishiguchi, H., et al., 'Unsteady Numerical Analysis of a Dual-Mode Scramjet Combustor with Cavity,' ISTS paper 2022-a-10, 2022.

Usage of JSS

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: N/A
• Number of Processes: 512 - 8192
• Elapsed Time per Case: 61 Hour(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 0.52

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 2021-January 2022