Control of Laminar Separation Bubbles via Plasma Actuators: a Preliminary Computational Study
Department
Mechanical and Aerospace Engineering
Major
Aerospace Engineering
Research Advisor
Finaish, Fathi
Advisor's Department
Mechanical and Aerospace Engineering
Funding Source
Missouri S&T Opportunities for Undergraduate Research Experiences (OURE) Program; NASA-Missouri Space Grant Consortium
Abstract
A parametric Computational Fluid Dynamics (CFD) study was conducted to examine the plausibility of a plasma actuator as a means of controlling a Laminar Separation Bubble (LSB) over an airfoil at low Reynolds numbers. In this study, the effects of altering the strength and location of a plasma actuator, modeled as a localized body force, on the size and location of the LSB and on the aerodynamic performance of the airfoil were observed. It was found that the body force, when properly located and with sufficient magnitude, could effectively eliminate the LSB. Additionally, it was found that by eliminating the LSB, the aerodynamic efficiency of the airfoil could be improved by over 60%. Thus, it was determined that plasma actuators may indeed be an effective measure for reducing or eliminating the negative effects associated with LSBs at low Reynolds numbers, making the technology an excellent candidate for future experimental research.
Biography
Justin Aholt is currently a senior in the Department of Mechanical and Aerospace Engineering at Missouri S&T. He intends to graduate with a Bachelor’s degree in Aerospace Engineering in May 2010, and a Master’s degree in May 2011.
Research Category
Engineering
Presentation Type
Oral Presentation
Document Type
Presentation
Location
Ozark Room
Presentation Date
07 Apr 2010, 9:30 am - 10:00 am
Control of Laminar Separation Bubbles via Plasma Actuators: a Preliminary Computational Study
Ozark Room
A parametric Computational Fluid Dynamics (CFD) study was conducted to examine the plausibility of a plasma actuator as a means of controlling a Laminar Separation Bubble (LSB) over an airfoil at low Reynolds numbers. In this study, the effects of altering the strength and location of a plasma actuator, modeled as a localized body force, on the size and location of the LSB and on the aerodynamic performance of the airfoil were observed. It was found that the body force, when properly located and with sufficient magnitude, could effectively eliminate the LSB. Additionally, it was found that by eliminating the LSB, the aerodynamic efficiency of the airfoil could be improved by over 60%. Thus, it was determined that plasma actuators may indeed be an effective measure for reducing or eliminating the negative effects associated with LSBs at low Reynolds numbers, making the technology an excellent candidate for future experimental research.
