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JAXA-SUBARU Cooperative Research

JAXA Supercomputer System Annual Report April 2019-March 2020

Report Number: R19ECMP10

Subject Category: Competitive Funding

PDF available here

  • Responsible Representative: Yasutada Tanabe, Aeronautical Technology Directorate, Aviation Systems Research Unit
  • Contact Information: Yasutada Tanabe(tan@chofu.jaxa.jp)
  • Members: Yasutada Tanabe, Hideaki Sugawara, Kuniyuki Takekawa, Masafumi Sasaki

Abstract

Compound helicopter is one of the next-generation rotorcraft to achieve high-speed flight. However, the increased drag due to the aerodynamic interaction between the rotor and the fixed-wing is one of the technology issues for this type of rotorcraft. The purpose of JAXA-SUBARU cooperative research is to clarify the amount of the drag increase and understand the interactive mechanism through wind-tunnel test and numerical simulation.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

There are many computational cases and the prior simulations for the wind-tunnel tests are required. To obtain simulation results efficiently, the supercomputer system is required.

Achievements of the Year

Wind-tunnel testing and numerical simulations are conducted for three different wings as shown in Fig.1. In the wind-tunnel tests, the rotor-test-stand affects the measurements of the aerodynamic forces significantly. The test data are corrected referring to the numerical simulation result where only simpler models are included. Figure 2 shows the comparison of the lift-to-drag ratio between the corrected test data and the simulation result. The summation of the isolated rotor and winged-body and the combined rotor/winged-body are compared in Fig. 2. There remains some discrepancies between the results of the tests and simulations, however, the reduction ratios of the lift-to-drag ratios are in good agreement between both results. The lift-to-drag ratio of the combined rotor/winged-body decreases by about 20% compared with the summation of isolated results. It is clarified that the aerodynamic drag increases significantly due to the aerodynamic interaction between the rotor and wing.

Annual Reoprt Figures for 2019

Fig.1: Models of the combined rotor and winged-body

 

Annual Reoprt Figures for 2019

Fig.2: Comparison of the results of the lift-to-drag ratio for the combined rotor/winged-body between the wind-tunnel test and the numerical simulation

 

Publications

N/A

Usage of JSS2

Computational Information

  • Process Parallelization Methods: N/A
  • Thread Parallelization Methods: OpenMP
  • Number of Processes: 1
  • Elapsed Time per Case: 336 Hour(s)

Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.24

 

Details

Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.

Computational Resources
System Name Amount of Core Time
(core x hours)
Fraction of Usage*2(%)
SORA-MA 49,563.41 0.01
SORA-PP 348,715.72 2.26
SORA-LM 3.84 0.00
SORA-TPP 162,833.95 9.83

 

File System Resources
File System Name Storage Assigned
(GiB)
Fraction of Usage*2(%)
/home 5,048.99 4.20
/data 16,667.34 0.29
/ltmp 4,764.44 0.40

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 7.94 0.20

*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.

JAXA Supercomputer System Annual Report April 2019-March 2020