TY - GEN
T1 - LES-based characterization of a suction and oscillatory blowing fluidic actuator
AU - Kim, Jeonglae
AU - Moin, Parviz
AU - Seifert, Avraham
N1 - Funding Information: The work of the first two authors has been supported by the Boeing company. The authors would like to thank Dr. Eran Arad (Rafael) for sharing valuable discussions. The first author also thank Jeff O’Brien, Dr. Luca Magri (Center for Turbulence Research) and Dr. Sanjeeb Bose (Cascade Technologies) for useful discussions regarding reduced-order modeling of the actuator. Computing resources are provided by the Argonne National Laboratory through the ASCR Leadership Computing Challenge. Publisher Copyright: © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA . All rights reserved.
PY - 2016
Y1 - 2016
N2 - Unsteady turbulent flows within a suction and oscillatory blowing actuator are simulated and characterized to provide better physical understanding of the complex actuator flows. Large-eddy simulation (LES) based upon a novel unstructured-grid technique is used to accurately calculate turbulent flows within the actuator. Simulations are performed for three inlet pressure conditions. Results show good agreement both qualitatively and quantitatively with the experimental measurement. The actuator is characterized by parameters such as pressure ratio, outlet velocity profile, oscillation frequency, suction to total flow rates. The LES-generated data are used to develop a reduced-order model applicable to integrated simulation of aerodynamic flow control as an unsteady boundary condition. Reduced-order modeling based upon dynamic mode decomposition (DMD) is employed to obtain a lower-order representation of the actuator outflows. Using two distinct dynamic modes, a sparsity-promoting variant of the standard DMD algorithm can describe unsteady flow fields at the actuator outlets with good accuracy.
AB - Unsteady turbulent flows within a suction and oscillatory blowing actuator are simulated and characterized to provide better physical understanding of the complex actuator flows. Large-eddy simulation (LES) based upon a novel unstructured-grid technique is used to accurately calculate turbulent flows within the actuator. Simulations are performed for three inlet pressure conditions. Results show good agreement both qualitatively and quantitatively with the experimental measurement. The actuator is characterized by parameters such as pressure ratio, outlet velocity profile, oscillation frequency, suction to total flow rates. The LES-generated data are used to develop a reduced-order model applicable to integrated simulation of aerodynamic flow control as an unsteady boundary condition. Reduced-order modeling based upon dynamic mode decomposition (DMD) is employed to obtain a lower-order representation of the actuator outflows. Using two distinct dynamic modes, a sparsity-promoting variant of the standard DMD algorithm can describe unsteady flow fields at the actuator outlets with good accuracy.
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U2 - 10.2514/6.2016-0572
DO - 10.2514/6.2016-0572
M3 - Conference contribution
SN - 9781624103933
T3 - 54th AIAA Aerospace Sciences Meeting
BT - 54th AIAA Aerospace Sciences Meeting
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA Aerospace Sciences Meeting, 2016
Y2 - 4 January 2016 through 8 January 2016
ER -