JAXA-SUBARU Cooperative Research
JAXA Supercomputer System Annual Report April 2019-March 2020
Report Number: R19ECMP10
Subject Category: Competitive Funding
- 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.

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
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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.
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 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 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