Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators
Abstract
:1. Introduction
2. Experiments
2.1. Experimental Apparatus
2.2. Experimental Conditions
2.3. Data Processing Method
3. Results and Discussion
3.1. Reliability of Aerodynamic Coefficients
3.2. Flow Control Effect
3.3. Flow Control Effect Sensitivity of Parameters
3.3.1. Freestream Velocity
3.3.2. Mean of the Angle of Attack
3.3.3. Reduced Frequency
3.3.4. Nondimensional Frequency of Pulse Voltage
3.3.5. Peak Pulse Voltage
3.3.6. Type of ns-DBDPA
3.3.7. Position of ns-DBDPA
4. Conclusions
- The lift coefficient increases by driving the ns-DBDPA when the model is pitching down;
- The aerodynamic coefficients corresponding to the frequency of the pulse voltage fluctuate when the ns-DBDPA is applied.
- The flow control effect appears under all conditions in which the freestream velocity, the angle of attack, and the reduced frequency were set to be from 40 m/s to 55 m/s, from 10 ± 10 deg to 15 ± 10 deg, and from 0.004 to 0.032, respectively;
- Changes in the freestream velocity have little effect on the flow control effect in the range we investigated;
- The flow control effect increases as the mean of the angle of attack and the reduced frequency decrease.
- The flow control effect increases as the nondimensional frequency of the pulse voltage decreases in the range we investigated, but the amplitude of the lift coefficient fluctuation increases;
- A sufficient flow control effect is obtained when the peak pulse voltage is greater than or equal to 3 kV;
- The flow control effect is sensitive to the shape of the leading edge. The best flow control effect is obtained when the position of the ns-DBDPA is 0% in the single-discharge type in the range we investigated.
Author Contributions
Funding
Acknowledgments
Conflicts of Interest
Appendix A. Selection of Oscillating Amplitude
(m/s) | (deg) | (deg) | k |
---|---|---|---|
50 | 8–10 | 8–10 | 0.032 |
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Case | (m/s) | (deg) | (deg) | k | (kV) | Type | (%) | |
---|---|---|---|---|---|---|---|---|
1 | 50 | 10 | 10 | 0.020 | - | - | - | - |
2 | 50 | 10 | 10 | 0.020 | 0.61 | 8.9 | Double | 0 |
3 | 40–55 | 10 | 10 | 0.020 | 0.61 | 8.9 | Double | 0 |
4 | 50 | 10–15 | 10 | 0.020 | 0.61 | 8.9 | Double | 0 |
5 | 50 | 10 | 10 | 0.004–0.032 | 0.13–0.96 | 8.9 | Double | 0 |
6 | 50 | 10 | 10 | 0.020 | 0.31–2.5 | 8.9 | Double | 0 |
7 | 50 | 10 | 10 | 0.032 | 0.48–1.9 | 8.9 | Double | 0 |
8 | 50 | 10 | 10 | 0.032 | 0.96 | 2–8.9 | Double | 0 |
9 | 50 | 10 | 10 | 0.032 | 0.48 | 8.9 | Double, single | 0 |
10 | 50 | 10 | 10 | 0.032 | 0.96 | 8.9 | Double, single | 0 |
11 | 50 | 10 | 10 | 0.032 | 0.96 | 8.9 | Single | 0–6 |
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Iwasaki, Y.; Nonomura, T.; Nankai, K.; Asai, K.; Kanno, S.; Suzuki, K.; Komuro, A.; Ando, A.; Takashima, K.; Kaneko, T.; et al. Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators. Energies 2020, 13, 1376. https://doi.org/10.3390/en13061376
Iwasaki Y, Nonomura T, Nankai K, Asai K, Kanno S, Suzuki K, Komuro A, Ando A, Takashima K, Kaneko T, et al. Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators. Energies. 2020; 13(6):1376. https://doi.org/10.3390/en13061376
Chicago/Turabian StyleIwasaki, Yuto, Taku Nonomura, Koki Nankai, Keisuke Asai, Shoki Kanno, Kento Suzuki, Atsushi Komuro, Akira Ando, Keisuke Takashima, Toshiro Kaneko, and et al. 2020. "Dynamic Stall Control around Practical Airfoil Using Nanosecond-Pulse-Driven Dielectric Barrier Discharge Plasma Actuators" Energies 13, no. 6: 1376. https://doi.org/10.3390/en13061376