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Numerical Simulations of Flow Separation Control in Low-Pressure Turbines using Plasma ActuatorsA recently introduced phenomenological model to simulate flow control applications using plasma actuators has been further developed and improved in order to expand its use to complicated actuator geometries. The new modeling approach eliminates the requirement of an empirical charge density distribution shape by using the embedded electrode as a source for the charge density. The resulting model is validated against a flat plate experiment with quiescent environment. The modeling approach incorporates the effect of the plasma actuators on the external flow into Navier Stokes computations as a body force vector which is obtained as a product of the net charge density and the electric field. The model solves the Maxwell equation to obtain the electric field due to the applied AC voltage at the electrodes and an additional equation for the charge density distribution representing the plasma density. The new modeling approach solves the charge density equation in the computational domain assuming the embedded electrode as a source therefore automatically generating a charge density distribution on the surface exposed to the flow similar to that observed in the experiments without explicitly specifying an empirical distribution. The model is validated against a flat plate experiment with quiescent environment.
Document ID
20080022317
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Suzen, Y. B.
(North Dakota State Univ. Fargo, ND, United States)
Huang, P. G.
(Wright State Univ. Dayton, OH, United States)
Ashpis, D. E.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
January 8, 2007
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
E-16992
AIAA Paper 2007-937
Report Number: E-16992
Report Number: AIAA Paper 2007-937
Meeting Information
Meeting: 45th AlAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 8, 2007
End Date: January 11, 2007
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NCC3-1040
CONTRACT_GRANT: NCC3-582
Distribution Limits
Public
Copyright
Public Use Permitted.
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