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MS_Thesis_Frankhouser_2015.pdf (8.46 MB)

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Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall

Frankhouser, Matthew William
http://rave.ohiolink.edu/etdc/view?acc_num=osu1449188933

Abstract Details

2015, Master of Science, Ohio State University, Aero/Astro Engineering.
Dynamic stall is a performance-limiting phenomenon experienced by rotorcraft in directional and maneuvering flight. Dynamic stall occurs on the retreating blade due to the high angles of attack that are experienced by the blades. Increasing the angle of attack is required to overcome the asymmetry of lift across the rotor disk that is a result from the velocity disparities between the advancing and retreating blade. This works sets out to study and improve the performance of a dynamically pitching NACA 0015 airfoil. The airfoil is subjected to both an incompressible and compressible flow field to simulate the dynamics of a rotor blade with cyclic pitching. In this experimental investigation of dynamic stall flow control, the effectiveness of nanosecond dielectric barrier discharge (NS-DBD) plasma actuation will be evaluated as a means to exert control authority. The NS-DBD plasma actuation is generated by a high-voltage magnetic compression pulsed power supply that was designed and built at The Ohio State University. To measure the influence of plasma actuation on the flow, surface pressures on the airfoil were measured through discrete pressure taps located on both the suction and pressure surfaces. The surface pressures are used to calculate the lift and moment during the dynamic pitching cycle. To visualize the compressibility effects in the outer flow, shadowgraph imagery was used to capture features in the flow around the leading edge of the test article. Tests were conducted at static and oscillating angles of attack at both Mach 0.2 and 0.4, and Reynolds numbers of 1.2 million and 2.2 million respectively. Pitch oscillations were conducted at reduced frequencies of k = 0.05. Actuation frequencies varied from non-dimensional frequencies (F + ) of 0.78 to 6.09. Surface pressures acquired at Mach 0.2 without actuation applied agreed with historical data at static angles of attack, validating that the application of the actuator had limited intrusiveness to the flow. When subjected to pitch oscillations, plasma actuation reduced the severity of lift and moment stall by altering the development of the dynamic stall vortex at Mach 0.2. At Mach 0.4, marginal improvements were gained through actuation. Excitation resulted in a strong dynamic stall vortex that convected more slowly in comparison to the baseline case. Shadowgraph imagery revealed lambda shock waves forming over the first 15 percent of the airfoil chord in the same proximity of th
James Gregory, PhD (Advisor)
Jeffrey Bons, PhD (Committee Member)
Mo Samimy, PhD (Committee Member)
120 p.
Aerospace Engineering
dynamic stall; nanosecond dielectric barrier discharge plasma actuation; flow control

Recommended Citations

Citations

  • Frankhouser, M. W. (2015). Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall [Master's thesis, Ohio State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=osu1449188933

    APA Style (7th edition)

  • Frankhouser, Matthew. Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall. 2015. Ohio State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=osu1449188933.

    MLA Style (8th edition)

  • Frankhouser, Matthew. "Nanosecond Dielectric Barrier Discharge Plasma Actuator Flow Control of Compressible Dynamic Stall." Master's thesis, Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1449188933

    Chicago Manual of Style (17th edition)

osu1449188933
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© 2015, all rights reserved.
This open access ETD is published by The Ohio State University and OhioLINK.