TY - GEN
T1 - Spatial growth of the spanwise disturbance induced by a synthetic jet on separation control over an airfoil
AU - Abe, Yoshiaki
AU - Nonomura, Taku
AU - Fujii, Kozo
PY - 2015/1/1
Y1 - 2015/1/1
N2 - The spatial growth of the spanwise disturbance induced by a synthetic jet is investigated on separated-flow control around NACA0015 (Re=63; 000 and AOA = 12: 0°) using a large-eddy simulation. The synthetic jet is installed at a leading edge which is numerically modeled by a three-dimensional deforming cavity: “Cavity model”; and an artificial jet profile for a boundary condition: “Bc model”. The jet profile of the Bc model is assumed to be sinusoidally oscillated in a spanwise direction with a wave number from kyin=2π = 0 to 95. In the Cavity model case, the modes around ky=2π= 20 to 30 are selectively amplified near the synthetic jet, which remains also in the turbulent boundary layer. In the Bc model cases, the most quick turbulent transition occurs in the case with kyin=2π = 30, where the coherent spanwise mode strongly remains in the turbulent boundary layer although its aerodynamic performance is not best. This result indicates that in the present condition, the spanwise disturbance of the jet profile does not always contribute to the higher aerodynamic performance even if it provides smooth and quick turbulent transition.
AB - The spatial growth of the spanwise disturbance induced by a synthetic jet is investigated on separated-flow control around NACA0015 (Re=63; 000 and AOA = 12: 0°) using a large-eddy simulation. The synthetic jet is installed at a leading edge which is numerically modeled by a three-dimensional deforming cavity: “Cavity model”; and an artificial jet profile for a boundary condition: “Bc model”. The jet profile of the Bc model is assumed to be sinusoidally oscillated in a spanwise direction with a wave number from kyin=2π = 0 to 95. In the Cavity model case, the modes around ky=2π= 20 to 30 are selectively amplified near the synthetic jet, which remains also in the turbulent boundary layer. In the Bc model cases, the most quick turbulent transition occurs in the case with kyin=2π = 30, where the coherent spanwise mode strongly remains in the turbulent boundary layer although its aerodynamic performance is not best. This result indicates that in the present condition, the spanwise disturbance of the jet profile does not always contribute to the higher aerodynamic performance even if it provides smooth and quick turbulent transition.
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U2 - 10.2514/6.2015-1057
DO - 10.2514/6.2015-1057
M3 - Conference contribution
AN - SCOPUS:84980359705
SN - 9781624103438
T3 - 53rd AIAA Aerospace Sciences Meeting
BT - 53rd AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 53rd AIAA Aerospace Sciences Meeting, 2015
Y2 - 5 January 2015 through 9 January 2015
ER -