Investigation on Transition Characteristics of a Modified RAE5243 Airfoil
The transition characteristics of a modified RAE5243 airfoil were investigated using a wind tunnel test and numerical simulations. Transition detection is of great significance for the assessment of drag reduction. In wind tunnel tests, transition location can be detected by infrared thermography. H...
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| Format: | Article |
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MDPI AG
2024-03-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/17/6/1489 |
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| author | Zhiyong Liu Hongbiao Wang Zhao Zhang Xiang Liu Fengxue Qian |
| author_facet | Zhiyong Liu Hongbiao Wang Zhao Zhang Xiang Liu Fengxue Qian |
| author_sort | Zhiyong Liu |
| collection | DOAJ |
| description | The transition characteristics of a modified RAE5243 airfoil were investigated using a wind tunnel test and numerical simulations. Transition detection is of great significance for the assessment of drag reduction. In wind tunnel tests, transition location can be detected by infrared thermography. However, in subsonic and transonic wind tunnel tests, the temperature difference between the laminar flow region and turbulent flow region is small. Moreover, the test models are usually made of metals, which make the transition location hard to identify. Combined with infrared thermography, a carbon nanotube heating coating powered by electricity was used to detect the transition location of a modified RAE5243 airfoil wing. The effects of heating power, angle of attack (AOA), and Mach number were studied. The results show that heating power has no impact on transition location. As the AOA increases, the transition location moves forward. With an increase in Mach number, the transition location moves forward first and then backward, and it reaches its most forward point at <i>Ma</i> = 0.75. The results of our numerical simulations indicate that, at <i>Ma</i><inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>≥</mo></mrow></semantics></math></inline-formula> 0.75, a shock wave appears on the wing, and the transition is closely related to the shock wave rather than the adverse pressure gradient. |
| first_indexed | 2024-04-24T18:20:37Z |
| format | Article |
| id | doaj.art-c23b14c4ce4545a7abf1ae70b08e68e1 |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-04-24T18:20:37Z |
| publishDate | 2024-03-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-c23b14c4ce4545a7abf1ae70b08e68e12024-03-27T13:35:53ZengMDPI AGEnergies1996-10732024-03-01176148910.3390/en17061489Investigation on Transition Characteristics of a Modified RAE5243 AirfoilZhiyong Liu0Hongbiao Wang1Zhao Zhang2Xiang Liu3Fengxue Qian4China Aerodynamics Research and Development Center, Mianyang 621000, ChinaChina Aerodynamics Research and Development Center, Mianyang 621000, ChinaChina Aerodynamics Research and Development Center, Mianyang 621000, ChinaChina Aerodynamics Research and Development Center, Mianyang 621000, ChinaChina Aerodynamics Research and Development Center, Mianyang 621000, ChinaThe transition characteristics of a modified RAE5243 airfoil were investigated using a wind tunnel test and numerical simulations. Transition detection is of great significance for the assessment of drag reduction. In wind tunnel tests, transition location can be detected by infrared thermography. However, in subsonic and transonic wind tunnel tests, the temperature difference between the laminar flow region and turbulent flow region is small. Moreover, the test models are usually made of metals, which make the transition location hard to identify. Combined with infrared thermography, a carbon nanotube heating coating powered by electricity was used to detect the transition location of a modified RAE5243 airfoil wing. The effects of heating power, angle of attack (AOA), and Mach number were studied. The results show that heating power has no impact on transition location. As the AOA increases, the transition location moves forward. With an increase in Mach number, the transition location moves forward first and then backward, and it reaches its most forward point at <i>Ma</i> = 0.75. The results of our numerical simulations indicate that, at <i>Ma</i><inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mo>≥</mo></mrow></semantics></math></inline-formula> 0.75, a shock wave appears on the wing, and the transition is closely related to the shock wave rather than the adverse pressure gradient.https://www.mdpi.com/1996-1073/17/6/1489transitioninfrared thermographycarbon nanotube coatinglaminar flowwind tunnel test |
| spellingShingle | Zhiyong Liu Hongbiao Wang Zhao Zhang Xiang Liu Fengxue Qian Investigation on Transition Characteristics of a Modified RAE5243 Airfoil Energies transition infrared thermography carbon nanotube coating laminar flow wind tunnel test |
| title | Investigation on Transition Characteristics of a Modified RAE5243 Airfoil |
| title_full | Investigation on Transition Characteristics of a Modified RAE5243 Airfoil |
| title_fullStr | Investigation on Transition Characteristics of a Modified RAE5243 Airfoil |
| title_full_unstemmed | Investigation on Transition Characteristics of a Modified RAE5243 Airfoil |
| title_short | Investigation on Transition Characteristics of a Modified RAE5243 Airfoil |
| title_sort | investigation on transition characteristics of a modified rae5243 airfoil |
| topic | transition infrared thermography carbon nanotube coating laminar flow wind tunnel test |
| url | https://www.mdpi.com/1996-1073/17/6/1489 |
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