JAXA Supercomputer System Annual Report (April 2018-March 2019)

Computational Simulations for Aircraft Modification Design in the FQUROH Project
Report Number: R18EA2800
Subject Category: Aeronautical Technology
URL: https://www.jss.jaxa.jp/en/ar/e2018/9078/
Responsible Representative
Kazuomi Yamamoto, FQUROH Project Team, Aeronautical Technology Directorate
Contact Information
Kazuomi Yamamoto (yamamoto.kazuomi@jaxa.jp)
Members
Kazuomi Yamamoto, Yasushi Ito, Takehisa Takaishi, Mitsuhiro Murayama, Ryotaro Sakai, Tohru Hirai, KentaroTanaka, Kazuhisa Amemiya, Gen Nakano, Takashi IshidaAbstract
The FQUROH project aims at raising the technical maturity level of the noise reduction technology for high-liftdevices and landing gear, which draws international attention to reduce noise in areas around airports, to a levelapplicable to future development of aircraft and related equipment. This contributes to reduction of aircraft noise
in local communities around the airport and airline operating costs by reducing landing fee. One of the objectivesof the FQUROH project is to verify the feasibility of practical noise reduction concepts and design methods basedon advanced computational simulations through modification of aircraft. Computational simulations wereperformed as part of the FQUROH project to understand Reynolds number effects resulting from wind tunnel
testing and to select low-noise and measuring devices that did not affect the flight performance of experimental
aircraft in an expected flight envelop.
Ref. URL: http://www.aero.jaxa.jp/eng/research/ecat/fquroh/
Reasons for using JSS2
The JSS2 enabled a large number of high-fidelity Reynolds-averaged Navier-Stokes (RANS) simulations withaerodynamically-important details in several flight configurations (different flap deflection angle settings, landing
gear positions, etc.) in the expected flight envelop (i.e., needs to consider several angles of attack, sideslip angles,etc.) to be conducted in a timely manner. The aerodynamic effect of low-noise and measuring devices was able tobe evaluate and quantified, which was difficult only with wind tunnel tests.
Achievements of the Year
Computational simulations were conducted to investigate and clarify results of the second flight demonstration
with JAXA’s jet research aircraft, “Hisho,” in 2017. RANS simulations with a laminar-to-turbulent transition
model were conducted for Hisho with noise reduction devices to investigate a tonal peak only found in the flight－25－

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JAXA Special Publication JAXA-SP-19-003E

demonstration. The flow around the flap side edges changed under flight and wind-tunnel Reynolds numbers(Fig. 1), and this result indicated that the generation of the tonal peak was due to the cavity flow only under theflight condition.
To improve our computational techniques for half-span wind tunnel models, RANS simulations were conducted
for the JAXA high-lift configuration standard model (JSM). It was found that the stall characteristics of the JSM
was affected by the boundary layer developed on the wind tunnel test section floor (Fig. 2).

Fig. 1: Investigation of Reynolds number effect using a transition model(turbulence kinetic energy distributions)Fig. 2: Normalized total pressure isosurface at 0.995 colored by wall distance at anangle of attack of 20.59 degrees (upper side and frontal views): (a) with free-air
condition; (b) with standoff and test section floor boundary layer (part of the test
section floor boundary layer, which is interrupted by the lower surface of the JSM,
flows around the wing)

Publications- Peer-reviewed papers
1) Ito, Y., Murayama, M., Yokokawa, Y., Yamamoto, K., Tanaka, K., Hirai, T., Yasuda, H., Tajima, A., and Ochi,
A., “JAXA’s and KHI’s Contribution to the Third High Lift Prediction Workshop,” Journal of Aircraft, 2019, pp.
2019/01/19, DOI:10.2514/1.C035131, in press.
- Non peer-reviewed papers
1) Yamamoto, K., Takaishi, T., Murayama, M., Yokokawa, Y., Ito, Y., Kohzai, M., Arizono, H., Sakai, R., Shoji,－26－This document is provided by JAXA.

JAXA Supercomputer System Annual Report (April 2018-March 2019)

H., Ueno, Y., Tsuchimoto, Y., Isotani, K., Hayama, K., Kumada, T., and Shimada, A., “FQUROH: A Flight
Demonstration Project for Airframe Noise Reduction Technology--the 2nd Flight Demonstration,” AIAA Paper
2018-4087, 2018 AIAA/CEAS Aeroacoustics Conference, Atlanta, GA, June 2018, DOI:10.2514/6.2018-4087.
2) Murayama, M., Yokokawa, Y., Ito, Y., Takaishi, T., Sakai, R., Yamamoto, K., Ueno, Y., Isotani, K.,
Tsuchimoto, Y., Hayama, K., Hirai, T., and Tanaka, K., “Noise Reduction Design for Flap Side-edges toward
FQUROH Second Flight Demonstration,” AIAA Paper 2018-4085, 2018 AIAA/CEAS Aeroacoustics Conference,Atlanta, GA, June 2018, DOI:10.2514/6.2018-4085.
3) Yokokawa, Y., Murayama, M., Takaishi, T., Ura, H., Kohzai, M., Ito, Y., Sakai, R., Yamamoto, K., Isotani, K.,
Ueno, Y., Tsuchimoto, Y., and Hayama, K., “Acoustic Wind Tunnel Test with 18% Scale Half-span Model toward
FQUROH Second Flight Demonstration,” AIAA Paper 2018-4086, 2018 AIAA/CEAS Aeroacoustics Conference,Atlanta, GA, June 2018, DOI:10.2514/6.2018-4086.
4) Kohzai, M., Yokokawa, Y., Takaishi, T., Ito, Y., Yamamoto, K., Omotani, H., Kato, T., and Hirai, T., “FlapSurface Pressure Measurements with 3D printed Pressure Belts in FQUROH Flight Demonstration,” AIAA Paper
2019-2111, AIAA Scitech 2019 Forum, San Diego, CA, January 2019, DOI:10.2514/6.2019-2111.
5) Ito, Y., Murayama, M., Yokokawa, Y., Yamamoto, K., Tanaka, K., and Hirai, T., “Wind Tunnel Interference
Effects on Japan Aerospace Exploration Agency’s Standard Model,” AIAA Paper 2019-2178, AIAA Scitech 2019
Forum, San Diego, CA, January 2019, DOI:10.2514/6.2019-2178.
Usage of JSS2
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Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

N/A

Number of Processes

1728

Elapsed Time per Case

40 Hour (s)Resources Used
Fraction of Usage in Total Resources*1 (%): 1.35
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

12,367,998.81

1.51

SORA-PP

3,431.47

0.03

SORA-LM

2.35

0.00

SORA-TPP

0.00

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JAXA Special Publication JAXA-SP-19-003E

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)

/home

82.16

0.09/data

9,422.64

0.17/ltmp

2,520.07

0.22

Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
268.299.39*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.

－28－This document is provided by JAXA.