TY - GEN
T1 - Wall-modeled large-eddy simulation of transonic buffet over a supercritical airfoil at high reynolds number
AU - Fukushima, Yuma
AU - Kawai, Soshi
N1 - Funding Information:
This work was supported in part by MEXT as a social and scientific priority issue (Development of Innovative Design and Production Processes that Lead the Way for the Manufacturing Industry in the Near Future) to be tackled by using post-K computer. A part of this research used computational resources of the K computer provided by the RIKEN Advanced Institute for Computational Science (Project ID:hp150254)
Publisher Copyright:
© 2017 by Yuma Fukushima and Soshi Kawai. Published by the American Institute of Aeronautics and Astronautics, Inc.
PY - 2017
Y1 - 2017
N2 - In this study, the wall-modeled large-eddy simulation (LES) of transonic buffet phenomena over the OAT15A supercritical airfoil is conducted. The computational results are compared with zonal detached eddy simulation (DES) and experiment. By using the wall-modeled LES, the buffet onset is successfully predicted. The small separation near the trailing edge is also accurately estimated with buffet phenomena. Velocity properties show good agreement with experiment except the region in which the shock wave moves. From the trace of the shock wave movement, the buffet frequency which nearly equals to experimental value is obtained. The self-sustained oscillation mechanisms are investigated from the computational results. As a results, Lee’s acoustic feedback loop model cannot predict the buffet frequency. On the other hand, the possibility of the proposed model is confirmed.
AB - In this study, the wall-modeled large-eddy simulation (LES) of transonic buffet phenomena over the OAT15A supercritical airfoil is conducted. The computational results are compared with zonal detached eddy simulation (DES) and experiment. By using the wall-modeled LES, the buffet onset is successfully predicted. The small separation near the trailing edge is also accurately estimated with buffet phenomena. Velocity properties show good agreement with experiment except the region in which the shock wave moves. From the trace of the shock wave movement, the buffet frequency which nearly equals to experimental value is obtained. The self-sustained oscillation mechanisms are investigated from the computational results. As a results, Lee’s acoustic feedback loop model cannot predict the buffet frequency. On the other hand, the possibility of the proposed model is confirmed.
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U2 - 10.2514/6.2017-0495
DO - 10.2514/6.2017-0495
M3 - Conference contribution
AN - SCOPUS:85017210277
T3 - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
BT - AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 55th AIAA Aerospace Sciences Meeting
Y2 - 9 January 2017 through 13 January 2017
ER -