Dielectric Barrier Discharge Control and Thrust Enhancement by Diode Surface Conference Paper uri icon

abstract

  • © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Increased interest in plasma assisted flow control is reflected by a dramatic increase in publication rate over the past decade, including numerous demonstrations of plasma-assisted flow control. Many of these have been summarized in several topical reviews published recently. For example, possibilities of supersonic flow control (including shock wave attenuation and shock configuration change) by plasma were discussed in [1]. Drag reduction at high speed by energy deposition was discussed in paper [2]. Boundary layer separation control by non-equilibrium non-thermal plasma was reviewed in [3] and [4]. In addition, the recent reviews [5, 6] includes many results of all mechanisms (thermal, electrostatic and MHD) related to applications for flow control in the subsonic and supersonic regimes. Conventional plasma actuators are based on applying AC sinusoidal voltages to induce dielectric barrier discharges. Such devices affect flows via induced velocities, or ion wind, that are typically less than 10 m/s. Due to the limited induced velocities produced by AC driven surface plasma devices, the primary focus of AC driven plasma based flow control has been on low freestream velocity (< 30 m/s) and low Reynolds number flows (Re ≤ 105). AC driven dielectric barrier devices have not yet been shown to exert sufficient control authority for alleviating helicopter retreating blade stall (RBS), which is characterized by free stream velocities on the order of 100 m/s (Mach 0.30) and Reynolds numbers on the order of 106 [6]. As an alternative to AC voltage inputs, nanosecond pulse driven plasma actuators in which voltage is applied in pulses at a specific frequency and with a specific on-time have been proposed for separated flow control [7-9]. Nanosecond pulsed periodic dielectric barrier devices have been experimentally demonstrated to affect separated flows over a range of Mach numbers (0.03 ≤ M ≤ 0.85) and Reynolds numbers (104 ≤ Re ≤ 2×106) that are consistent with retreating blade flows. Furthermore, the nanosecond pulsed actuators tested to date have required less than 10 Watt per cm. of wing span [9], and therefore are energy efficient. Current paper discusses a research on new nanosecond pulse driven surface plasma devices for enhanced control authority in high speed air.

author list (cited authors)

  • Starikovskiy, A., & Miles, R. B.

citation count

  • 0

publication date

  • January 1, 2017 11:11 AM
  • January 2017