JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0007

• Responsible Representative: Yoshikazu Makino(Next Generation Aeronautical Innovation Hub Center, Aeronautical Technology Directorate)
• Contact Information: Yoshikazu Makino(makino@chofu.jaxa.jp)
• Members: Junichi Akatsuka, Naoko Tokugawa, Hiroaki Ishikawa, Yoshine Ueda, Yuriko Kakei, Takuya Makimoto, Yoshikazu Makino, Dongyoun Kwak, Keisuke Ohira, Atsushi Ueno, Satoshi Kondo, Tatsunori Yuhara
• Subject Category: Aviation(Aircraft)

Abstract

The system integration design technologies for achieving low sonic-boom, low aerodynamic drag, low landing and take-off noise, and light weight simultaneously are the key technologies for future supersonic airplanes. JAXA is promoting the R&D for these technologies based on our experiences of demonstrating the advanced low-drag and low-boom design concepts.

Goal

Please refer ‘D-SEND project / Silent supersonic transport technology | Sky Frontier – Sky Frontier Program | Aeronautical Technology Directorate‘.

Objective

Please refer ‘D-SEND project / Silent supersonic transport technology | Sky Frontier – Sky Frontier Program | Aeronautical Technology Directorate‘.

References and Links

Please refer ‘D-SEND project / Silent supersonic transport technology | Sky Frontier – Sky Frontier Program | Aeronautical Technology Directorate‘.

Use of the Supercomputer

In the R&D for system integration of silent supersonic airplane technologies, the airplane design study of a small-size civil supersonic transport is conducted. Simulations for evaluating the aerodynamic performance and noise characteristics are conducted using JAXA supercomputer system.

Necessity of the Supercomputer

To achieve low sonic-boom, low aerodynamic drag, low landing and take-off noise, and light weight simultaneously, the multi-objective optimization tools are utilized in the design study. The super computer is necessary to obtain the multiple objective function efficiently with many numerical simulations.

Achievements of the Year

A numerical simulation of the sonic boom prediction of some configuration as a part of 2nd AIAA Sonic Boom Prediction Workshop is conducted in order to improve the numerical accuracy. CFD analysis of the 3 models using JAXA’s TAS solver were performed and their results were almost same as the other participant’s results.

Fig.1:Cp distribution of low boom model

Publications

Presentations

1) Ishikawa,H., Ueda,Y., and Tokugawa,N., ‘Natural Laminar Flow Wing Design for a Low-Boom supersonic Aircraft,’ 55th AIAA Aerospace Sciences Meeting, AIAA SciTech Forum, Grapevine, Texas, AIAA 2017-1860, 2017

Computational Information

• Parallelization Methods: Hybrid Parallelization
• Process Parallelization Methods: MPI
• Thread Parallelization Methods: Automatic Parallelization
• Number of Processes: 16
• Number of Threads per Process: 32
• Number of Nodes Used: 16
• Elapsed Time per Case (Hours): 1
• Number of Cases: 350

Resources Used

Total Amount of Virtual Cost(Yen): 16,940,064

Breakdown List by Resources

Note: Virtual Cost=amount of cost, using the unit price list of JAXA Facility Utilization program(2016)

JAXA Supercomputer System Annual Report April 2016-March 2017