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Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators

Rethmel, Christopher C.

Abstract Details

2011, Master of Science, Ohio State University, Mechanical Engineering.
This work continues an ongoing development and use of dielectric barrier discharge (DBD) plasma actuators driven by repetitive nanosecond pulses for high Reynolds number aerodynamic flow control. These actuators are believed to influence the flow via a thermal mechanism which is fundamentally different from the more commonly studied AC-DBD plasmas. Leading edge separation control on an 8-inch chord NACA 0015 airfoil is demonstrated at various post-stall angles of attack (α) for Reynolds numbers (Re) and Mach numbers (M) up to 1,150,000 and 0.26, respectively (free stream velocity = 93 m/s). The nanosecond pulse driven DBD can extend the stall angle at low Re by functioning as an active trip. At post-stall α, the device generates coherent spanwise vortices that transfer momentum from the freestream to the separated region, thus reattaching the flow. This is observed for all Re and M spanning the speed range of the subsonic tunnel used in this work. A comparison of leading edge separation control between NS-DBD and AC-DBD plasma actuation demonstrates the increased control authority of NS-DBD plasma at higher flow speeds. The actuator is also integrated into a feedback control system with a stagnation-line-sensing hot film on the airfoil pressure side. A simple on/off type controller that operates based on a threshold of the mean value of the power dissipated by the hot film is developed for this system. A preliminary extremum seeking controller is also investigated for dynamically varying Re. Several challenges typically associated with integration of DBD plasma actuators into a feedback control system have been overcome. The most important of these is the demonstration of control authority at realistic takeoff and landing Re and M.
Dr. Mo Samimy, PhD (Advisor)
Dr. James Gregory, PhD (Committee Member)
80 p.

Recommended Citations

Citations

  • Rethmel, C. C. (2011). Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators [Master's thesis, Ohio State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=osu1306348260

    APA Style (7th edition)

  • Rethmel, Christopher. Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators. 2011. Ohio State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=osu1306348260.

    MLA Style (8th edition)

  • Rethmel, Christopher. "Airfoil Leading Edge Flow Separation Control Using Nanosecond Pulse DBD Plasma Actuators." Master's thesis, Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1306348260

    Chicago Manual of Style (17th edition)