Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft
The nanosecond pulsed plasma discharge actuator is used on a flying wing aircraft. At the angles of attack rang from -4° to 28°, the impact of plasma actuator arrangement position and discharge frequency on lift-enhancement effect is tested. Oil flow visualization is used to investigate the surface...
| Format: | Article |
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| Language: | zho |
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EDP Sciences
2018-10-01
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| Series: | Xibei Gongye Daxue Xuebao |
| Subjects: | |
| Online Access: | https://www.jnwpu.org/articles/jnwpu/pdf/2018/05/jnwpu2018365p963.pdf |
| _version_ | 1797642671193325568 |
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| collection | DOAJ |
| description | The nanosecond pulsed plasma discharge actuator is used on a flying wing aircraft. At the angles of attack rang from -4° to 28°, the impact of plasma actuator arrangement position and discharge frequency on lift-enhancement effect is tested. Oil flow visualization is used to investigate the surface flow pattern varies with angles of attack for the plasma actuator turned on and off. The result indicates that lift-enhancement can be achieved through the actuator discharges at large angles of attack on flying wing aircraft. The arrangement position and discharge frequency both have a significant impact on lift-enhancement effect. The actuator which arranged at the leading edge of the aircraft could get the best lift-enhancement effect. There exists an optimal discharge frequency, flow separation under this frequency can be effectively suppressed, which results the best lift-enhancement effect. The flow visualization test shows that the control mechanisms of the plasma actuator are to inject energy to the shear layer, thus increased the vortex strength. The vortices strengthen the mixing of the outer high-speed fluid with inner low-speed fluid, which effectively restrains the separation. |
| first_indexed | 2024-03-11T14:03:39Z |
| format | Article |
| id | doaj.art-c6fd564392204e3d90242ae91da4b344 |
| institution | Directory Open Access Journal |
| issn | 1000-2758 2609-7125 |
| language | zho |
| last_indexed | 2024-03-11T14:03:39Z |
| publishDate | 2018-10-01 |
| publisher | EDP Sciences |
| record_format | Article |
| series | Xibei Gongye Daxue Xuebao |
| spelling | doaj.art-c6fd564392204e3d90242ae91da4b3442023-11-02T03:27:40ZzhoEDP SciencesXibei Gongye Daxue Xuebao1000-27582609-71252018-10-0136596396910.1051/jnwpu/20183650963jnwpu2018365p963Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft01234Beijing Electro-Mechanical Engineering InstituteBeijing Electro-Mechanical Engineering InstituteBeijing Electro-Mechanical Engineering InstituteCollege of Aerospace Engineering, Nanjing University of Aeronautics and AstronauticsCollege of Aerospace Engineering, Nanjing University of Aeronautics and AstronauticsThe nanosecond pulsed plasma discharge actuator is used on a flying wing aircraft. At the angles of attack rang from -4° to 28°, the impact of plasma actuator arrangement position and discharge frequency on lift-enhancement effect is tested. Oil flow visualization is used to investigate the surface flow pattern varies with angles of attack for the plasma actuator turned on and off. The result indicates that lift-enhancement can be achieved through the actuator discharges at large angles of attack on flying wing aircraft. The arrangement position and discharge frequency both have a significant impact on lift-enhancement effect. The actuator which arranged at the leading edge of the aircraft could get the best lift-enhancement effect. There exists an optimal discharge frequency, flow separation under this frequency can be effectively suppressed, which results the best lift-enhancement effect. The flow visualization test shows that the control mechanisms of the plasma actuator are to inject energy to the shear layer, thus increased the vortex strength. The vortices strengthen the mixing of the outer high-speed fluid with inner low-speed fluid, which effectively restrains the separation.https://www.jnwpu.org/articles/jnwpu/pdf/2018/05/jnwpu2018365p963.pdfplasma actuatorflying winglift-enhancementoil flowangle of attackflow separationflow visualizationwind tunnel experiment |
| spellingShingle | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft Xibei Gongye Daxue Xuebao plasma actuator flying wing lift-enhancement oil flow angle of attack flow separation flow visualization wind tunnel experiment |
| title | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft |
| title_full | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft |
| title_fullStr | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft |
| title_full_unstemmed | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft |
| title_short | Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft |
| title_sort | effects of plasma actuator discharge on lift enhancement and flow patterns of flying wing aircraft |
| topic | plasma actuator flying wing lift-enhancement oil flow angle of attack flow separation flow visualization wind tunnel experiment |
| url | https://www.jnwpu.org/articles/jnwpu/pdf/2018/05/jnwpu2018365p963.pdf |