TY - GEN
T1 - Large-eddy simulation of pseudo-shock wave in a square duct
AU - Lee, S.
AU - Watanabe, J.
AU - Kouchi, T.
AU - Takita, K.
AU - Masuya, G.
PY - 2012/12/1
Y1 - 2012/12/1
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.
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M3 - Conference contribution
AN - SCOPUS:84880997199
SN - 9781600869310
T3 - 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
BT - 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
T2 - 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Y2 - 24 September 2012 through 28 September 2012
ER -