TY - GEN
T1 - Suppression of vortex shedding from a circular cylinder by using a traveling wave wall
AU - Chen, Wenli
AU - Liu, Yang
AU - Hu, Hui
AU - Xu, Feng
AU - Li, Hui
N1 - Publisher Copyright:
© 2015 American Institute of Aeronautics and Astronautics Inc. All rights reserved.
PY - 2014
Y1 - 2014
N2 - An experimental study was conducted to suppress the unsteady vortex shedding from a circular cylinder by using a traveling wave wall (TWW). The leeward surfaces of the circular cylinder model were replaced by wave surfaces, which can move to form symmetrical TWW when driven by a motor system. The propagation speed of the wave was adjustable by controlling the rotational speed of the motor. During the experiments, while the oncoming wind speed was fixed at U∞=9.1 m/s, the propagation speed of the TWW was adjusted to have the ratio between of the wave propagation speed and the oncoming wind speed varied from 0 (i.e., stationary case) to 0.167. It was found that, with the TWW control, the wake region behind the cylinder model was found to be shortened and the vortex shedding from the cylinder model was weakened greatly. The average drag force acting on the test model was also found to be reduced significantly. Two different mechanisms, i.e., “forced perturbation mechanism” and “resonant perturbation mechanism”, were found to play important roles for the TWW flow control.
AB - An experimental study was conducted to suppress the unsteady vortex shedding from a circular cylinder by using a traveling wave wall (TWW). The leeward surfaces of the circular cylinder model were replaced by wave surfaces, which can move to form symmetrical TWW when driven by a motor system. The propagation speed of the wave was adjustable by controlling the rotational speed of the motor. During the experiments, while the oncoming wind speed was fixed at U∞=9.1 m/s, the propagation speed of the TWW was adjusted to have the ratio between of the wave propagation speed and the oncoming wind speed varied from 0 (i.e., stationary case) to 0.167. It was found that, with the TWW control, the wake region behind the cylinder model was found to be shortened and the vortex shedding from the cylinder model was weakened greatly. The average drag force acting on the test model was also found to be reduced significantly. Two different mechanisms, i.e., “forced perturbation mechanism” and “resonant perturbation mechanism”, were found to play important roles for the TWW flow control.
UR - https://www.scopus.com/pages/publications/85088358359
U2 - 10.2514/6.2014-0399
DO - 10.2514/6.2014-0399
M3 - 会议稿件
AN - SCOPUS:85088358359
T3 - 52nd Aerospace Sciences Meeting
BT - 52nd Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 52nd Aerospace Sciences Meeting 2014
Y2 - 13 January 2014 through 17 January 2014
ER -