Abstract
Wind tunnel experiments are conducted for improving the aerodynamic performance of delta wing using a leading-edge pulsed nanosecond dielectric barrier discharge (NS-DBD). The whole effects of pulsed NS-DBD on the aerodynamic performance of the delta wing are studied by balanced force measurements. Pressure measurements and particle image velocimetry (PIV) measurements are conducted to investigate the formation of leading-edge vortices affected by the pulsed NS-DBD, compared to completely stalled flow without actuation. Various pulsed actuation frequencies of the plasma actuator are examined with the freestream velocity up to 50 m/s. Stall has been delayed substantially and significant shifts in the aerodynamic forces can be achieved at the post-stall regions when the actuator works at the optimum reduced frequency of F + = 2. The upper surface pressure measurements show that the largest change of static pressure occurs at the forward part of the wing at the stall region. The time-averaged flow pattern obtained from the PIV measurement shows that flow reattachment is promoted with excitation, and a vortex flow pattern develops. The time-averaged locations of the secondary separation line and the center of the vortical region both move outboard with excitation.
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Abbreviations
- c :
-
Wing root chord length
- x, y, z :
-
Chordwise coordinate system
- Re :
-
Reynolds number based on the root chord length
- f :
-
Pulsed actuation frequency (Hz)
- F + :
-
Reduced excitation frequency (=fc/U ∞ )
- Cd :
-
Drag force coefficient
- Cl :
-
Lift force coefficient
- U ∞ :
-
Freestream velocity (m/s)
- p :
-
Static pressure on the model surface (Pa)
- C p :
-
Pressure coefficient
- V p−p :
-
Applied voltage to the plasma actuator (peak-to-peak) (kilovolt, kV)
- α :
-
Angle of attack (°)
- Λ :
-
Wing leading-edge sweep back angle (°)
- ∞ :
-
Freestream condition
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Acknowledgments
This work is founded by National Natural Science Foundation of China under contract Nos. 51336011, 51276197, and 51207169. The authors would like to thank Lei Chang for helpful discussion about the results. These supports are gratefully acknowledged.
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Zhao, Gy., Li, Yh., Liang, H. et al. Control of vortex on a non-slender delta wing by a nanosecond pulse surface dielectric barrier discharge. Exp Fluids 56, 1864 (2015). https://doi.org/10.1007/s00348-014-1864-8
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DOI: https://doi.org/10.1007/s00348-014-1864-8