Abstract
Large-eddy simulation (LES) of Pseudo-Shock Wave (PSW) in a square duct was perfomed to study the three-dimensional turbulent structure. A flow with the PSW in the square section duct produced by the high back pressure was reproduced using LES. The inflow Mach number was 2.5 and the inflow boundary layer of 4.2mm thick. The incoming boundary layer for a square duct was established using the multi rescaling method. The Mach number distribution, schlieren image, wall pressure, and velocity data obtained from the LES were compared with the past experimental data. The shock train structure observed in the experiment was well reproduced by the LES. The averaged wall pressure and streamwise velocity distributions agreed well between the LES and the experiments. Also, the distributions of intensity and spatial correlation of velocity fluctuation reasonably agreed between the LES and the experiment, although some differences were observed in the velocity fluctuation intensity distribution at the position of front shock wave.
| Original language | English |
|---|---|
| Title of host publication | 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 |
| Publication status | Published - 2012 |
| Event | 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 - Tours, France Duration: Sep 24 2012 → Sep 28 2012 |
Other
| Other | 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 |
|---|---|
| Country | France |
| City | Tours |
| Period | 9/24/12 → 9/28/12 |
Fingerprint
ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
- Control and Systems Engineering
Cite this
Large-eddy simulation of pseudo-shock wave in a square duct. / Lee, S.; Watanabe, J.; Kouchi, Toshinori; Takita, K.; Masuya, G.
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 2012.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Large-eddy simulation of pseudo-shock wave in a square duct
AU - Lee, S.
AU - Watanabe, J.
AU - Kouchi, Toshinori
AU - Takita, K.
AU - Masuya, G.
PY - 2012
Y1 - 2012
N2 - Large-eddy simulation (LES) of Pseudo-Shock Wave (PSW) in a square duct was perfomed to study the three-dimensional turbulent structure. A flow with the PSW in the square section duct produced by the high back pressure was reproduced using LES. The inflow Mach number was 2.5 and the inflow boundary layer of 4.2mm thick. The incoming boundary layer for a square duct was established using the multi rescaling method. The Mach number distribution, schlieren image, wall pressure, and velocity data obtained from the LES were compared with the past experimental data. The shock train structure observed in the experiment was well reproduced by the LES. The averaged wall pressure and streamwise velocity distributions agreed well between the LES and the experiments. Also, the distributions of intensity and spatial correlation of velocity fluctuation reasonably agreed between the LES and the experiment, although some differences were observed in the velocity fluctuation intensity distribution at the position of front shock wave.
AB - Large-eddy simulation (LES) of Pseudo-Shock Wave (PSW) in a square duct was perfomed to study the three-dimensional turbulent structure. A flow with the PSW in the square section duct produced by the high back pressure was reproduced using LES. The inflow Mach number was 2.5 and the inflow boundary layer of 4.2mm thick. The incoming boundary layer for a square duct was established using the multi rescaling method. The Mach number distribution, schlieren image, wall pressure, and velocity data obtained from the LES were compared with the past experimental data. The shock train structure observed in the experiment was well reproduced by the LES. The averaged wall pressure and streamwise velocity distributions agreed well between the LES and the experiments. Also, the distributions of intensity and spatial correlation of velocity fluctuation reasonably agreed between the LES and the experiment, although some differences were observed in the velocity fluctuation intensity distribution at the position of front shock wave.
UR - http://www.scopus.com/inward/record.url?scp=84880997199&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84880997199&partnerID=8YFLogxK
M3 - Conference contribution
SN - 9781600869310
BT - 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
ER -