Volume 40 Issue 8
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LI Yueqiang, GAO Chao, WU Bin, et al. Turbulent boundary layer control with spanwise DBD plasma actuators[J]. Journal of Aerospace Power, 2025, 40（8）：20230170 doi: 10.13224/j.cnki.jasp.20230170
Citation: LI Yueqiang, GAO Chao, WU Bin, et al. Turbulent boundary layer control with spanwise DBD plasma actuators[J]. Journal of Aerospace Power, 2025, 40（8）：20230170 doi: 10.13224/j.cnki.jasp.20230170
shu

Turbulent boundary layer control with spanwise DBD plasma actuators

doi: 10.13224/j.cnki.jasp.20230170

  • School of Aeronautics，Northwestern Polytechnical University，Xi’an 710072，China

  • Received Date: 2023-03-20
    Available Online: 2025-05-22
    Abstract

  • The flat plate turbulent boundary layer control by spanwise dielectric barrier discharge (DBD) plasma at Reτ = 1 140 was investigated, and the drag reduction and boundary layer profiles were measured using hot-wire technology. Result showed that, the skin fraction drag with plasma control decreased downstream of the center of two adjacent upper electrodes, and with the increase of duty cycle, the drag reduction increased first and then decreased, reaching a maximum as the duty cycle was 0.5. Meanwhile, the velocity in the inner region of the boundary layer (y+<200) decreased. In the downstream position of the upper electrode, the drag increased with plasma control, the drag reduction decreased almost linearly with the increase of duty cycle, and the velocity in the inner region of the boundary layer (y+<100) increased. The control effect gradually weakened as it moved away from the actuators, and the control effect basically disappeared around 1.27δ downstream of the actuators.

     

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