TY - GEN
T1 - Unsteady flow simulation around two-wheel main landing gear based on compressible navier-stokes solver with immersed boundary method
AU - Imamura, Taro
AU - Tamaki, Yoshiharu
N1 - Funding Information:
The LEG geometry was kindly provided by Aeronautical Technology Directorate of Japan Aerospace Exploration Agency. Author would like to express his gratitude for their contribution. This work was supported by JSPS KAKENHI grant numbers 23760767 (Grant-in-Aid for Young Scientists (B)) and 15H05559 (Grant-in-Aid for Young Scientists (A)). Also, this research was conducted using the SGI Rackable C2112-4GP3/C1102-GP8 (Reedbush-U) in the Information Technology Center, The University of Tokyo.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - A hierarchical Cartesian-grid-based flow solver which have the capability to model the turbulent boundary layer using immersed boundary method with a wall function is used to investigate the flow around a realistic landing gear model developed by Japan Aerospace Exploration Agency. The calculations are performed on three different grid resolutions to understand the grid dependencies. The cell number of the finest case is around 82 million, and the statistical data is obtained within two days including grid generation. The overall flow field around the complex geometry is investigated in detail based on the time-averaged flow field. The results show favorable agreement with the experimental data.
AB - A hierarchical Cartesian-grid-based flow solver which have the capability to model the turbulent boundary layer using immersed boundary method with a wall function is used to investigate the flow around a realistic landing gear model developed by Japan Aerospace Exploration Agency. The calculations are performed on three different grid resolutions to understand the grid dependencies. The cell number of the finest case is around 82 million, and the statistical data is obtained within two days including grid generation. The overall flow field around the complex geometry is investigated in detail based on the time-averaged flow field. The results show favorable agreement with the experimental data.
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U2 - 10.2514/6.2020-2579
DO - 10.2514/6.2020-2579
M3 - Conference contribution
AN - SCOPUS:85092462212
SN - 9781624105982
T3 - AIAA AVIATION 2020 FORUM
BT - AIAA AVIATION 2020 FORUM
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA AVIATION 2020 FORUM
Y2 - 15 June 2020 through 19 June 2020
ER -