JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0114

• Responsible Representative: Eiichi Sato(Department of Space Flight Systems, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency)
• Contact Information: Akira Oyama(oyama2@flab.isas.jaxa.jp)
• Members: Daniele Sirigatti, Akira Oyama, Dong Lee, Taufik Sulaiman, Hiroaki Fukumoto, Yuta Ozawa, Daisuke Kato, Takuya Harada, Hiroaki Nakano, Takara Watanabe, Goichi Kawasaki, Shota Inoue
• Subject Category: Space(Space engineering)

Abstract

Objective of this research is to conduct fundamental research on high-speed fluid dynamics required in the field of space engineering. In this fiscal year, we study wall-model for high Reynolds number flow computation and fluid control devices that may significantly reduce aerodynamic drag of space transportation systems.

Goal

Objective is to conduct research on high speed fluid dynamics required for future technology in space engineering field.

Objective

Goal of this research is to obtain knowledge and technology related to high speed aerodynamics required for future technology in the field of space engineering.

This fiscal year, we develop a numerical simulation method for high Reynolds number flow to accurately estimate aerodynamic performance of space transportation system and conduct research on fluid control device that may significantly improve aerodynamic performance of space transportation system.

References and Links

Please refer 'FLAB-HOME PAGE'.

Use of the Supercomputer

In this research, we develop numerical flow simulation technology for high Reynolds number flow and research on fluid control devices currently attracting worldwide attention. In both cases, Large Eddy Simulation (LES) is required because flow involves flow separation and reattachment. In addition, for aerodynamic design such space transportation system, it is necessary to perform calculations for many designs and evaluate their performance. Therefore, we use a supercomputer to conduct this research.

Necessity of the Supercomputer

In this research, we develop numerical flow simulation technology for high Reynolds number flow and research on fluid control devices currently attracting worldwide attention. In both cases, Large Eddy Simulation (LES) is required because flow involves flow separation and reattachment. In addition, for aerodynamic design such space transportation system, it is necessary to perform calculations for many designs and evaluate their performance. Therefore, a supercomputer is required to conduct this research.

Achievements of the Year

Objective of this research is to conduct fundamental research on high-speed fluid dynamics required in the field of space engineering. In this fiscal year, we study wall-model for high Reynolds number flow computation and fluid control devices that may significantly reduce aerodynamic drag of space transportation systems.

(1) Wall-model for high Reynolds number flow condition

Flow phenomena around us are often in high Reynolds number conditions and turbulent boundary layer is usually formed. In order to accurately capture such flow field characteristics using numerical simulations, it is necessary to use so-called the wall-model which correctly models a turbulent boundary layer as well as the Large Eddy Simulation (LES) using high-order accuracy schemes. In this study, we construct a simulation code that can automatically switch the wall-model from an instantaneous physical quantity. Then, we apply it to the flow field around airfoils and verify the engineering usefulness of the model.

(2) Control of dynamic flowfield of rotating blades using DBD plasma actuator

Flow around rotating blades used for helicopters and windmills are dynamic flowfield, in which the airflow condition dynamically changes. Flow control in such condition is effective for improvement of efficiency and safety. Although DBD plasma actuators are expected to be promising as control devices for dynamic flow fields in recent years, the fluid control mechanism of DBD plasma actuators in dynamic flow fields has not been well organized. In this study, we conduct numerical simulation to clarify effective fluid control mechanism of DBD plasma actuator in dynamic flowfield.

Fig.1(1):Instantaneous flowfield of airfoil obtained by LES with wall-model.

Fig.1(2):Promotion of recovery from dynamic stall condition using DBD plasma actuator(Left: flow with no control right: flow controlled by DBD plasma actuator)

Publications

Peer-reviewed articles

1) D. Lee, T. Nonomura, A. Oyama, K. Fujii, 'Comparative studies of numerical methods for evaluating aerodynamic characteristics of two-dimensional airfoil at low Reynolds numbers,' International Journal of Computational Fluid Dynamics, Taylor & Francis, Vol.30, pp57-67, 2017.

2) H. Fukumoto, H. Aono, T. Watanabe, M. Tanaka, H. Matsuda, T, Osako, T. Nonomura, A.Oyama and K. Fujii, 'Control of Dynamic Flowfield around a Pitching NACA 633−618 airfoil by a DBD plasma actuator,' International Journal of Heat and Fluid Flow, ELSEVIER, Volume 62, Part A, December 2016, Pages 10–23, December, 2016.:

Presentations

1) Taku Nonomura, Akira Oyama, Kozo Fujii, Koichi Morihira, Gabriel Pichon, and Daiki Terakado, 'Effects of Disturbed Nozzle-exit Boundary Layers on Acoustic Waves from Ideally-Expandedsupersonic Jet,' 22nd AIAA/CEAS Aeroacoustics Conference, Lyon, France, 30 May - 1 June, 2016.

2) Daiki Terakado, Taku Nonomura, Akira Oyama, and Kozo Fujii, 'Mach Number Dependence on Sound Sources in High Mach Number Turbulent Mixing Layer,' 22nd AIAA/CEAS Aeroacoustics Conference, Lyon, France, 30 May - 1 June, 2016.

3) Daisuke Kato, Taku Nonomura and Akira Oyama, 'Quantitative evaluation of the acoustic waves generated by a supersonic impinging jet,' 5th Joint Meeting of the Acoustical Society of America and Acoustical Society of Japan, Honolulu, Hawaii, Nov 28- Dec 2, 2016

4) D. Lee, T. Nonomura, A. Oyama, K. Fujii, 'Formation mechanisms of rapid pressure recovery around a laminar separation bubble,' American Physical Society 69th Annual Meeting Division of Fluid Dynamics, Portland, USA. 20 Nov. 2016 – 22 Nov. 2016.

5) D. Lee, T. Nonomura, A. Oyama, K. Fujii, 'Effects of cross-sectional aspect ratio of flat plate on flow characteristics,' The 24th International Congress of Theoretical and Applied Mechanics, Montreal, Canada, 21 Aug. 2016 – 26 Aug. 2016

6) K. Asano, M. Sato, T. Nonomura, A. Oyama and K. Fujii, 'Control of Airfoil Flow at Cruise Condition by DBD Plasma Actuator- Sophisticated Airfoil vs. Simple Airfoil with Flow Control -,' AIAA Aviation 2016, AIAA website, AIAA-2016-3624, Washington D.C., June 13, 2016 – June 17, 2016.

7) H. Fukumoto, H. Aono, T. Nonomura, A. Oyama and K. Fujii, 'Control of Dynamically Stalled Flowfield around a Pitching Airfoil by DBD Plasma Actuator,' the AIAA Aviation and Aeronautics Forum and Exposition 2016, Washington, D.C., June 13-17. 2016.

Computational Information

• Parallelization Methods: Hybrid Parallelization
• Process Parallelization Methods: MPI
• Thread Parallelization Methods: OpenMP
• Number of Processes: 38, 25
• Number of Threads per Process: 32
• Number of Nodes Used: 1216, 800
• Elapsed Time per Case (Hours): 50, 75
• Number of Cases: 3, 10

Resources Used

Total Amount of Virtual Cost(Yen): 31,134,952

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