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REDUCED ORDER MODELING OF FLOW OVER A NACA 0015 AIRFOIL FOR FUTURE CONTROL APPLICATION

Sullivan, Taylor D

Abstract Details

2014, Master of Science, Miami University, Physics.
Reduced order models that can capture and predict general flow characteristics are essential for closed-loop flow control around aerodynamic bodies. This research tests Galerkin based reduced order models using proper orthogonal decomposition modes derived experimentally to predict the flow over a NACA-0015 airfoil. Each of the models is tested on the airfoil at incident angles ranging from α=20° to α=10° for the baseline flow and a flow forced at 1250 Hz by nanosecond dielectric barrier discharge plasma actuators. It was found that both reduced order models were most successful in using 8 ≤n≤12 POD modes for their calculations.
Edgar Caraballo, PhD (Advisor)
Michael Pechan, PhD (Committee Member)
T. William Houk, PhD (Committee Member)
Andrew Sommers, PhD (Committee Member)
90 p.

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Citations

  • Sullivan, T. D. (2014). REDUCED ORDER MODELING OF FLOW OVER A NACA 0015 AIRFOIL FOR FUTURE CONTROL APPLICATION [Master's thesis, Miami University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=miami1407295741

    APA Style (7th edition)

  • Sullivan, Taylor. REDUCED ORDER MODELING OF FLOW OVER A NACA 0015 AIRFOIL FOR FUTURE CONTROL APPLICATION . 2014. Miami University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=miami1407295741.

    MLA Style (8th edition)

  • Sullivan, Taylor. "REDUCED ORDER MODELING OF FLOW OVER A NACA 0015 AIRFOIL FOR FUTURE CONTROL APPLICATION ." Master's thesis, Miami University, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=miami1407295741

    Chicago Manual of Style (17th edition)