Loading...

Experimental investigation of the active flow control over a cranked-delta wing

Mahdavi Zafarghandi, F ; Sharif University of Technology | 2024

40 Viewed
  1. Type of Document: Article
  2. DOI: 10.2514/1.C037347
  3. Publisher: 2024
  4. Abstract:
  5. A series of experiments was carried out to investigate the effects of active flow control on the aerodynamic characteristics of a cranked-delta-wing model at a subsonic speed. A dielectric barrier discharge (DBD) plasma actuator was used to improve the aerodynamic performance of the half-span cranked-delta-wing model at various angles of attack. The model had inboard and outboard sweepback angles of 57 and 38 deg, respectively. The surface pressure distribution was obtained at five streamwise stations and at two ray stations. All data were obtained at a constant Reynolds number of 0.27 × 106 and at various angles of attack: 0 deg ≤ α ≤ 36 deg. The results showed that the pulsed DBD plasma actuator improved the aerodynamic performance of the cranked-delta-wing model by preventing flow separation at high angles of attack. The deep stall angle of attack was delayed up to 6 deg, and the poststall suction coefficient was increased approximately 30% at an angle of attack of about α 34 deg when the pulsed DBD plasma was applied at its optimum condition (F ≈ 1 and duty cycle 10%). It was found that the pulsed plasma actuator suppressed the wake flow in the forward portion of the wing at poststall angles of attack, thus delaying the flow separation. However, the effects of the DBD actuator at very high angles of attack on the flow reattachment process at the rear portion of the wing for the present DBD setting were seen to be minimal. The induced flow by the pulsed DBD plasma actuator influenced the vortex merging phenomena and delayed the onset of the outer vortex burst at prestall angles of attack. © 2023 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved
  6. Keywords:
  7. Actuators ; Delta wing aircraft ; Dielectric barrier discharge ; Dielectric devices ; Dielectric materials ; Flow control ; Flow separation ; Reynolds number ; Vortex flow ; Wings ; Active flow control ; Aero-dynamic performance ; Delta wing model ; Dielectric barrier discharge plasma actuators ; Dielectric barrier discharges ; Experimental investigations ; High angles of attack ; Pulsed dielectric barrier discharges ; Angle of attack
  8. Source: Journal of Aircraft ; Volume 61, Issue 1 , 2024 , Pages 73-85 ; 00218669 (ISSN)
  9. URL: https://arc.aiaa.org/doi/10.2514/1.C037347