Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition
In order to upsurge the maneuverability of micro aerial vehicles, a tubercle leading edge inspired by the whale flipper was applied as a passive stall control method. Although this method could be useful to control stall phenomena, the effect of geometrical properties on the flow physic should be in...
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| Format: | Article |
| Language: | English |
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Isfahan University of Technology
2023-07-01
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| Series: | Journal of Applied Fluid Mechanics |
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| Online Access: | https://www.jafmonline.net/article_2258_2c7657f110d9be4316e3194167eb323a.pdf |
| _version_ | 1797790069495431168 |
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| author | A. Nikkhoo A. Esmaeili |
| author_facet | A. Nikkhoo A. Esmaeili |
| author_sort | A. Nikkhoo |
| collection | DOAJ |
| description | In order to upsurge the maneuverability of micro aerial vehicles, a tubercle leading edge inspired by the whale flipper was applied as a passive stall control method. Although this method could be useful to control stall phenomena, the effect of geometrical properties on the flow physic should be investigated to reach the root of them. According to preceding research, the effect of some parameters on the tubercle leading edge wing is a hot topic among researchers. The aim of this research is to explore the effects of sectional wing geometries like amplitude, wavelength, thickness, maximum thickness location, and camber on the aerodynamic feature of full-span tubercle leading edge wing, particularly at 22 degree in post-stall circumstances. The results present that by reducing the amplitude about 2.5%c, the lift coefficient upsurges by about 3.5%; instead, the drag coefficient reduces about 6%. On the other hand, by decreasing the wavelength from 46.2%c to 11.7%c, the drag coefficient and the lift coefficient decrease by about 15% and 19%, respectively. Furthermore, as the thickness rises from 10.55%c to 18.14%c, the lift and drag coefficient goes down about 9.4% and 2.9%, respectively. Furthermore, by increasing the camber from 2.56%c to 3.34%c, the lift to drag ratio goes down by about 1.06%. Finally, by raising the last design variable (maximum thickness location) from 0.26c to 0.51c, the lift to drag ratio increases about 13.7%. |
| first_indexed | 2024-03-13T01:59:30Z |
| format | Article |
| id | doaj.art-9401fdce1a814f74858472cde72c6074 |
| institution | Directory Open Access Journal |
| issn | 1735-3572 1735-3645 |
| language | English |
| last_indexed | 2024-03-13T01:59:30Z |
| publishDate | 2023-07-01 |
| publisher | Isfahan University of Technology |
| record_format | Article |
| series | Journal of Applied Fluid Mechanics |
| spelling | doaj.art-9401fdce1a814f74858472cde72c60742023-07-02T07:41:51ZengIsfahan University of TechnologyJournal of Applied Fluid Mechanics1735-35721735-36452023-07-011691752176610.47176/jafm.16.09.17552258Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall ConditionA. Nikkhoo0A. Esmaeili1Mechanical Engineering Department, Faculty of Engineering, Ferdowsi University of Mashhad, IranMechanical Engineering Department, Faculty of Engineering, Ferdowsi University of Mashhad, IranIn order to upsurge the maneuverability of micro aerial vehicles, a tubercle leading edge inspired by the whale flipper was applied as a passive stall control method. Although this method could be useful to control stall phenomena, the effect of geometrical properties on the flow physic should be investigated to reach the root of them. According to preceding research, the effect of some parameters on the tubercle leading edge wing is a hot topic among researchers. The aim of this research is to explore the effects of sectional wing geometries like amplitude, wavelength, thickness, maximum thickness location, and camber on the aerodynamic feature of full-span tubercle leading edge wing, particularly at 22 degree in post-stall circumstances. The results present that by reducing the amplitude about 2.5%c, the lift coefficient upsurges by about 3.5%; instead, the drag coefficient reduces about 6%. On the other hand, by decreasing the wavelength from 46.2%c to 11.7%c, the drag coefficient and the lift coefficient decrease by about 15% and 19%, respectively. Furthermore, as the thickness rises from 10.55%c to 18.14%c, the lift and drag coefficient goes down about 9.4% and 2.9%, respectively. Furthermore, by increasing the camber from 2.56%c to 3.34%c, the lift to drag ratio goes down by about 1.06%. Finally, by raising the last design variable (maximum thickness location) from 0.26c to 0.51c, the lift to drag ratio increases about 13.7%.https://www.jafmonline.net/article_2258_2c7657f110d9be4316e3194167eb323a.pdffull-span tubercle leading edge wing geometrical parametersflow separation area (fsa)air dry zone aerodynamic forcespower spectral density (psd)fast fourier transform (fft) |
| spellingShingle | A. Nikkhoo A. Esmaeili Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition Journal of Applied Fluid Mechanics full-span tubercle leading edge wing geometrical parameters flow separation area (fsa) air dry zone aerodynamic forces power spectral density (psd) fast fourier transform (fft) |
| title | Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition |
| title_full | Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition |
| title_fullStr | Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition |
| title_full_unstemmed | Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition |
| title_short | Numerical Study of Geometrical Properties of Full-Span Tubercle Leading Edge Wing at Post-Stall Condition |
| title_sort | numerical study of geometrical properties of full span tubercle leading edge wing at post stall condition |
| topic | full-span tubercle leading edge wing geometrical parameters flow separation area (fsa) air dry zone aerodynamic forces power spectral density (psd) fast fourier transform (fft) |
| url | https://www.jafmonline.net/article_2258_2c7657f110d9be4316e3194167eb323a.pdf |
| work_keys_str_mv | AT anikkhoo numericalstudyofgeometricalpropertiesoffullspantubercleleadingedgewingatpoststallcondition AT aesmaeili numericalstudyofgeometricalpropertiesoffullspantubercleleadingedgewingatpoststallcondition |