本文へ移動

サイトナビゲーションへ移動

検索ボックスへ移動

サイドバーへ移動

ここは、本文エリアの先頭です。

Numerical Fluid Analysis of Supersonic Flying Vehicle

JAXA Supercomputer System Annual Report February 2022-January 2023

Report Number: R22EACA20

Subject Category: JSS Inter-University Research

PDF available here

  • Responsible Representative: Keiichi Kitamura, Associate Professor, Yokohama National University
  • Contact Information: Motoki Magara, Yokohama National University(magara-motoki-tb@ynu.jp)
  • Members: Yoshikatsu Furusawa, Keiichi Kitamura, Motoki Magara, Kazuki Nimura

Abstract

Supersonic parachutes, which are an effective means of deceleration for planetary exploration, and rockets, which are a means of space transportation, fly at supersonic speeds. The unsteady flow around the supersonic parachute and the protrusions on the rocket surface are factors that hinder the stable flight of supersonic vehicles. The effects of these factors on aerodynamic characteristics are not yet clear, and there is a limit to the knowledge that can be obtained from wind tunnel tests. Therefore, numerical analysis of supersonic parachutes and rockets with protrusions is performed to obtain aerodynamic data under supersonic velocity conditions.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

In this research, it is necessary to accurately capture the complex flow field around supersonic parachutes of the DGB and DS types and the vortex around the projectile of a rocket with a projectile, and numerical calculations using a high-resolution computational grid require a large amount of cost. Therefore, a supercomputer capable of performing large-scale calculations in a short period of time is required.

Achievements of the Year

Aerodynamic Characteristics of Supersonic Parachutes

Numerical analysis was performed for two types of supersonic parachutes with opening area of the DGB and DS types shown in Fig.1, assuming a uniform flow Mach number of 2.0, to consider the effect of the angle of attack. As a result, it was found that when the canopy angle of attack is small, the DS type has a smaller drag coefficient variation than the DGB type, but the local pressure difference, as shown in Fig. 2, may cause damage.

Aerodynamic characteristics of a rocket with protuberance

One protuberance was attached to the downwind side of the forward part of the body, and the height and width of the protuberance were varied by 5% of the diameter of the body, respectively, for an elongated body with a slenderness ratio of 8.9, as shown in Fig. 3. The uniform flow Mach number was set to 1.5 and the angle of attack to 15 deg.. Interesting results were obtained when only the width of the protuberance was varied, as shown in Fig. 3. It is clear that the vortex asymmetry does not change when the protuberance width is varied, nor does the side force.

Annual Reoprt Figures for 2022

Fig.1: Model for Analysis

 

Annual Reoprt Figures for 2022

Fig.2: Pressure

 

Annual Reoprt Figures for 2022

Fig.3: Model for Analysis

 

Annual Reoprt Figures for 2022

Fig.4: Visualization of vortices

 

Publications

– Oral Presentations

1) Nimura,K., Tsutsui, F., Kitamura, K., and Nonaka, S,”Numerical Analysis on Effect of Surface Protuberance Sizes on Side Force of Supersonic Slender Body”,54th Conference on Fluid Dynamics / 40th Symposium on Aerospace Numerical Simulation Technology (Aiina: Iwate Prefecture Information Exchange Center, Morioka City, June 29, 2022)

2) Nimura,K., Tsutsui, F., Kitamura, K., and Nonaka, S.: Aerodynamic Effects of Surface Protuberance Sizes on Slender-Bodied Supersonic Vehicle, AIAA-2023-0241, AIAA SciTech Forum 2023, National Harbor, MD & Online, Jan.2023

– Poster Presentations

1)Magara,M., Kitamura, K., :Numerical Flow Analysis on Pressure Fluctuations inside and outside Supersonic Parachutes with Different Canopy Configurations, 66th Space Science and Technology Conference, Novenber 1st-4th 2022.

Usage of JSS

Computational Information

  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: Automatic Parallelization
  • Number of Processes: 512 – 2048
  • Elapsed Time per Case: 72 Hour(s)

JSS3 Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.28

 

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 5216651.52 0.23
TOKI-ST 56531.96 0.06
TOKI-GP 0.00 0.00
TOKI-XM 0.00 0.00
TOKI-LM 222734.66 14.93
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 260.33 0.24
/data and /data2 40980.00 0.32
/ssd 4336.67 0.60

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 24.89 0.11

*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)
4306.61 3.00

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

JAXA Supercomputer System Annual Report February 2022-January 2023