Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor
A feedback control system for mitigating flow separation was developed by using a string-type dielectric-barrier-discharge (DBD) plasma actuator and a fiber Bragg grating (FBG) sensor. Tangential jets were induced from the string-type DBD plasma actuator, which was located at 5% chord from the leadi...
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| Format: | Article |
| Language: | English |
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Wiley
2016-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2016/8648919 |
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| _version_ | 1849685050175520768 |
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| author | Takehiko Segawa Daiki Suzuki Takayasu Fujino Timothy Jukes Takayuki Matsunuma |
| author_facet | Takehiko Segawa Daiki Suzuki Takayasu Fujino Timothy Jukes Takayuki Matsunuma |
| author_sort | Takehiko Segawa |
| collection | DOAJ |
| description | A feedback control system for mitigating flow separation was developed by using a string-type dielectric-barrier-discharge (DBD) plasma actuator and a fiber Bragg grating (FBG) sensor. Tangential jets were induced from the string-type DBD plasma actuator, which was located at 5% chord from the leading edge of an NACA0024 airfoil. The FBG sensor was attached to the interior surface near the root of the cantilever beam modeled on the pressure surface of the airfoil. The strain at the cantilever root was reflected in the form of Bragg wavelengths (λB) detected by the FBG sensor when the cantilever tip was vibrated by the flow near the trailing edge of the airfoil. It was found that calculating running standard deviations in the Bragg wavelength (λB′) detected by the sensor was valuable for judging flow separation in real time. The feedback control of flow separation on the NACA0024 airfoil was successfully demonstrated by setting λB′=0.0028 with periodic flow separations generated in a wind tunnel by oscillating a side wall of the test section with frequency fw=0.42 Hz. It was confirmed that the appearance probability of flow separation tends to decrease with a decrease in the duration for calculating λB′ and with an increase in the duration of jet injection. |
| format | Article |
| id | doaj-art-b9be7470d48142db9cfe9323ad39ee26 |
| institution | DOAJ |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2016-01-01 |
| publisher | Wiley |
| record_format | Article |
| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-b9be7470d48142db9cfe9323ad39ee262025-08-20T03:23:16ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742016-01-01201610.1155/2016/86489198648919Feedback Control of Flow Separation Using Plasma Actuator and FBG SensorTakehiko Segawa0Daiki Suzuki1Takayasu Fujino2Timothy Jukes3Takayuki Matsunuma4Research Institute for Energy Conservation, National Institute of Advanced Industrial Science and Technology (AIST), 1-2-1 Namiki, Tsukuba, Ibaraki 305-8564, JapanResearch Institute for Energy Conservation, National Institute of Advanced Industrial Science and Technology (AIST), 1-2-1 Namiki, Tsukuba, Ibaraki 305-8564, JapanFaculty of Engineering, Information and Systems, University of Tsukuba, 1-1-1 Tennodai, Tsukuba, Ibaraki 305-8577, JapanDepartment of Engineering, University of Nottingham, University Park, Nottingham NG7 2RD, UKResearch Institute for Energy Conservation, National Institute of Advanced Industrial Science and Technology (AIST), 1-2-1 Namiki, Tsukuba, Ibaraki 305-8564, JapanA feedback control system for mitigating flow separation was developed by using a string-type dielectric-barrier-discharge (DBD) plasma actuator and a fiber Bragg grating (FBG) sensor. Tangential jets were induced from the string-type DBD plasma actuator, which was located at 5% chord from the leading edge of an NACA0024 airfoil. The FBG sensor was attached to the interior surface near the root of the cantilever beam modeled on the pressure surface of the airfoil. The strain at the cantilever root was reflected in the form of Bragg wavelengths (λB) detected by the FBG sensor when the cantilever tip was vibrated by the flow near the trailing edge of the airfoil. It was found that calculating running standard deviations in the Bragg wavelength (λB′) detected by the sensor was valuable for judging flow separation in real time. The feedback control of flow separation on the NACA0024 airfoil was successfully demonstrated by setting λB′=0.0028 with periodic flow separations generated in a wind tunnel by oscillating a side wall of the test section with frequency fw=0.42 Hz. It was confirmed that the appearance probability of flow separation tends to decrease with a decrease in the duration for calculating λB′ and with an increase in the duration of jet injection.http://dx.doi.org/10.1155/2016/8648919 |
| spellingShingle | Takehiko Segawa Daiki Suzuki Takayasu Fujino Timothy Jukes Takayuki Matsunuma Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor International Journal of Aerospace Engineering |
| title | Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor |
| title_full | Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor |
| title_fullStr | Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor |
| title_full_unstemmed | Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor |
| title_short | Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor |
| title_sort | feedback control of flow separation using plasma actuator and fbg sensor |
| url | http://dx.doi.org/10.1155/2016/8648919 |
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