Research and development of prediction technology for thermal and aerodynamic characteristics of hypersonic vehicle

JAXA Supercomputer System Annual Report February 2022-January 2023

Report Number: R22EDA201G20

Subject Category: Aeronautical Technology

Responsible Representative: Yasuhiro Mizobuchi, Aviation Technology Directorate, Aircraft Lifecycle Innovation Hub
Contact Information: matsuyama.shingo@jaxa.jp(matsuyama.shingo@jaxa.jp)
Members: Keisuke Fujii, Shingo Matsuyama, Hidemi Takahashi, Takahiro Yamamoto

Abstract

Strong shock waves are generated around a flying object at hypersonic speeds, and the high-temperature gas compressed by the shock waves causes strong heat transfer to the hypersonic vehicle. The objective of this research is to establish a technique to reproduce such a flow field around a hypersonic vehicle by CFD and to accurately evaluate the aerodynamics and heating applied to the vechicle.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

The flight conditions of hypersonic vehicles often have high Reynolds numbers, which necessitates the evaluation of turbulent heating. Since this study aims to evaluate turbulent heating with high accuracy using Direct Numerical Simulation (DNS) and Large Eddy Simulation (LES), a three-dimensional unsteady analysis is inevitably required. The computational cost of such a large-scale three-dimensional analysis is very high, and analysis using a supercomputer is essential.

Achievements of the Year

Turbulent transitions in boundary layers in hypersonic flows are still a difficult problem to predict. In order to clarify the mechanism of turbulent transition and to obtain data to construct a prediction model of the transition, a DNS was conducted for the turbulent transition in a flat boundary layer at M=5. Figure 1 show the analysis of the process of turbulent transition of the boundary layer on the two plates placed facing each other. The DNS analysis shows that the turbulent boundary layer is generated by an artificial disturbance on the lower plate, and that the noise emitted by the turbulent boundary layer reaches the boundary layer on the upper plate, causing a turbulent transition.

Fig.1: DNS of turbulent transitions occurring in the boundary layer on two flat plates placed facing each other (Mach 5).

Publications

N/A

Usage of JSS

Computational Information

Process Parallelization Methods: MPI
Thread Parallelization Methods: OpenMP, Automatic Parallelization
Number of Processes: 500 – 4000
Elapsed Time per Case: 150 Hour(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 1.99

Details

Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.

Computational Resources
System Name	CPU Resources Used (Core x Hours)	Fraction of Usage*2(%)
TOKI-SORA	53651316.60	2.34
TOKI-ST	58872.35	0.06
TOKI-GP	0.00	0.00
TOKI-XM	0.00	0.00
TOKI-LM	33862.03	2.27
TOKI-TST	0.00	0.00
TOKI-TGP	0.00	0.00
TOKI-TLM	0.00	0.00

File System Resources
File System Name	Storage Assigned (GiB)	Fraction of Usage*2(%)
/home	276.74	0.25
/data and /data2	3656.65	0.03
/ssd	674.93	0.09

Archiver Resources
Archiver Name	Storage Used (TiB)	Fraction of Usage*2(%)
J-SPACE	1.94	0.01

*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

ISV Software Licenses Resources
	ISV Software Licenses Used (Hours)	Fraction of Usage*2(%)
ISV Software Licenses (Total)	463.62	0.32

*2: Fraction of Usage：Percentage of usage relative to each resource used in one year.