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Flowfield around blades with optimized airfoil for six-roter Mars helicopter

JAXA Supercomputer System Annual Report February 2021-January 2022

Report Number: R21ECMP14

Subject Category: Competitive Funding

PDF available here

  • Responsible Representative: Yoshikazu Makino, Aeronautical Technology Directorate, Silent Supersonic Aircraft Team
  • Contact Information: Masahiro Kanazaki, Tokyo Metropolitan University(kana@tmu.ac.jp)
  • Members: Masahiro Kanazaki, Daisuke Kikuchi, Yuki Kishi, Keita Kimura, Masahiko Sugiura, Hideaki Sugawara, Kuniyuki Takekawa, Yasutada Tanabe

Abstract

In this project, a study was conducted to find the optimum blade shape for a 6-rotor helicopter for Mars exploration, The optimization method by Efficient Global Optimization and the airfoil definition method by Class Shape Transformation were employed. The two-dimensional calculation by FaSTAR was used for the evaluation during the optimization, and rFLow3D was used to evaluate the performance as a rotor blade. The aerodynamic performance of CLF5605 airfoil adopted by Ingenuity at NASA JPL was referenced and compared, and the airfoil named TMU21k3-1, which improved the aerodynamic performance was obtained.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

In order to effectively employ the JAXA-provided tools, FaSTAR and rFlow3D, it was necessary to run on the JAXA supercomputer, which has many application examples and is well-tuned.

Achievements of the Year

The optimization method by Efficient Global Optimization and the airfoil definition method by Class Shape Transformation were employed. The two-dimensional calculation by FaSTAR was used for the evaluation during the optimization, and rFLow3D was used to evaluate the performance as a rotor blade. Referring to the aerodynamic performance of CLF5605 airfoil adopted by Ingenuity at NASA JPL, we were able to obtain an airfoil TMU21k3-1 which achived better hovering perfomance than that of CLF5605 (Figs. 1 and 2).

Annual Reoprt Figures for 2021

Fig.1: Visualization results around 6-roter which employed the optimal airfoil, TMU21k3-01

 

Annual Reoprt Figures for 2021

Fig.2: CT-FoM diagram of the roter blade airfoil designed this year.The optimal design of the blade airfoil has resulted in a blade airfoil that outperforms the existing airfoil (CLF5605).Figure of Merit was calculated by 3D calculation using rFlow3D.

 

Publications

N/A

Usage of JSS

Computational Information

  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: OpenMP
  • Number of Processes: 36
  • Elapsed Time per Case: 96 Hour(s)

JSS3 Resources Used

 

Fraction of Usage in Total Resources*1(%): 0.31

 

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 445107.73 0.02
TOKI-ST 1935150.66 2.38
TOKI-GP 0.00 0.00
TOKI-XM 0.00 0.00
TOKI-LM 583.66 0.04
TOKI-TST 322004.80 6.76
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 2155.31 2.14
/data and /data2 32767.23 0.35
/ssd 1668.94 0.43

 

Archiver Resources
Archiver Name Storage Used
(TiB)
Fraction of Usage*2(%)
J-SPACE 10.76 0.07

*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)
51.68 0.04

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

JAXA Supercomputer System Annual Report February 2021-January 2022