Influence of a reverse delta-type add-on device on wake vortex alleviation
Particle image velocimetry was used in a low-speed wind tunnel to investigate the effect of interactions of vortices produced by a wingtip of a half-span wing (NACA 23012 in landing configuration) and a slender reverse delta-type add-on device placed near the tip on the upper surface of the half-spa...
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| Main Authors: | , , , |
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| Format: | Article |
| Language: | English English English |
| Published: |
American Institute of Aeronautics and Astronautics Inc. (AIAA)
2016
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| Subjects: | |
| Online Access: | http://irep.iium.edu.my/53914/9/53914_Influence%20of%20a%20Reverse%20Delta-Type_new%20text.pdf http://irep.iium.edu.my/53914/10/53914_Influence%20of%20a%20Reverse%20Delta-Type.pdf_WOS.pdf http://irep.iium.edu.my/53914/11/53914_Influence%20of%20a%20Reverse%20Delta-Type.pdf_SCOPUS.pdf http://irep.iium.edu.my/53914/ https://arc.aiaa.org/doi/pdf/10.2514/1.J054436 |
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| Summary: | Particle image velocimetry was used in a low-speed wind tunnel to investigate the effect of interactions of vortices produced by a wingtip of a half-span wing (NACA 23012 in landing configuration) and a slender reverse delta-type add-on device placed near the tip on the upper surface of the half-span wing. This work investigates the characteristics of the vortex interactions generated downstream in planes perpendicular to the freestream direction and their dependence on angles of attack at a chord-based Reynolds number of Rec = 2.75 × 105. It was found that the add-on device significantly reduced the tangential velocity, vorticity, and circulation magnitude by up to 82.9, 92.6, and 42.8%, respectively, and increased the resultant vortex core radius by a factor of 6.57.Asix-component force balance was used to obtain the aerodynamic performance of the half-span wing model with a reverse delta-type add-on device. It was found that the reverse delta-type add-on device marginally affected the aerodynamic performance of the halfspan high-lift configuration wing model. |
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