Research on the future transportation technology

JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0074

Responsible Representative: Koichi Okita(Research and Development Directorate, Unit IV)
Contact Information: Susumu Hasegawa(hasegawa.susumu@jaxa.jp)
Members: Susumu Hasegawa
Subject Category: Space(Space transportation)

Abstract

The aerodynamic characteristics of the airframe and the engine of the spaceplane which integrates the them will be clarified. Taking into consideration of the movement of the center of gravity, the aerodynamic center and the change of the engine thrust under the various flight conditions from take-off to high speed, aerodynamic characteristics of the spaceplane were investigated numerically and experimentally.

Goal

The establishment of technologies for airframe/engine integration of the spaceplane for the realization of future space transportation technology

Objective

The coupled aerodynamic characteristics between airframe and engine of the spaceplane on the flight condition from takeoff to high speed was to be elucidated.

References and Links

N/A

Use of the Supercomputer

The comparison between the experimental data obtained by wind tunnel tests and the numerical results were conducted and verified. After the verifications of numerical results, various aerodynamic data which are difficult to obtain by experiments are computed and analyzed by CFD.

Necessity of the Supercomputer

The number of wind tunnel tests is limited, and the data obtained are limited. Therefore, after verification of numerical results, data which are difficult to obtain by wind tunnel test can be obtained. By using higher-performance computer, more reliable data can be obtained and the development of spaceplane technology are accelerated.

Achievements of the Year

Correspondent numerical calculations of spaceplane performed by wind tunnel experiment were carried out. The features of aerodynamic coefficients are consistent, but some data do not agree quantitatively. Larger data analysis will be conducted and its data are verified. After that, it is planned to perform numerical analysis which are difficult to obtain in the wind tunnel tests.

Fig.1:Streamlines and Mach numbers around the splaceplane for the flight condition of Mach 1.3

Publications

Presentations

1) Susumu Hasegawa, Takeshi Kanda,’Preliminary Numerical Simulation of Flow around Spaceplane for Airframe Engine Integration’, ISTS 31th, Matsuyama, Japan, Jun 9, 2017.

Computational Information

Parallelization Methods: Process Parallelization
Process Parallelization Methods: MPI
Thread Parallelization Methods: n/a
Number of Processes: 128
Number of Threads per Process: 1
Number of Nodes Used: 4
Elapsed Time per Case (Hours): 256
Number of Cases: 100

Resources Used

Total Amount of Virtual Cost(Yen): 968,378

Breakdown List by Resources

Computational Resources
System Name	Amount of Core Time(core x hours)	Virtual Cost(Yen)
SORA-MA	29,829.72	49,062
SORA-PP	101,166.72	863,761
SORA-LM	0.00	0
SORA-TPP	0.00	0

SORA-FS File System Resources
File System Name	Storage assigned(GiB)	Virtual Cost(Yen)
/home	6.68	62
/data	4,768.37	44,980
/ltmp	976.56	9,211

J-SPACE Archiving System Resources
Archiving System Name	Storage used(TiB)	Virtual Cost(Yen)
J-SPACE	0.42	1,299

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