Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number
The instability of flapping wing aircrafts makes them difficult to control. As it is challenging to control and puts passengers at risk, it is not currently employed in modern aircraft technology. This study aims to analyze the aerodynamic coefficients of flapping wing aircraft at different flapping...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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Aerospace Society Malaysia
2023
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| Online Access: | http://psasir.upm.edu.my/id/eprint/107583/1/107583.pdf |
| _version_ | 1811137794564685824 |
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| author | Mowhoub, Mohamed Abdullah, Ermira Junita |
| author_facet | Mowhoub, Mohamed Abdullah, Ermira Junita |
| author_sort | Mowhoub, Mohamed |
| collection | UPM |
| description | The instability of flapping wing aircrafts makes them difficult to control. As it is challenging to control and puts passengers at risk, it is not currently employed in modern aircraft technology. This study aims to analyze the aerodynamic coefficients of flapping wing aircraft at different flapping angles in order to understand their effects on the aircrafts stability. XFLR5 software was used to calculate the aerodynamics coefficients and longitudinal derivatives in different range of flapping angles from 40° to -40°. This range of flapping angles has been selected for the purpose of this study based on the physical limitations of a mechanical vehicle. Theoretically, an aircraft without a tail is unstable because the main function of a tail is to produce a moment that counters the moment produced by the wings to balance the aircraft. In the presented research, a model has been designed with and without tail, and modeled using XFLR5 to produce the aerodynamics coefficients. Then, MATLAB software was used to develop the longitudinal flight dynamics for the model. The results show that the longitudinal motion is stable for the range of flapping angle between 40° to -40°. The natural frequency increases as flapping angle changes from 0° to 40° and from 0° to -40°. In the meantime, for the short period modes eigenvalue, the real part moves toward the origin as the flapping angle changes from 0° to 40° and from 0° to -40°. On the other hand, for the phugoid modes eigenvalue, the real part moves away from the origin to the left half plane as the flapping angle changes from 0° to 40° and from 0° to -40°. |
| first_indexed | 2024-09-25T03:39:58Z |
| format | Article |
| id | upm.eprints-107583 |
| institution | Universiti Putra Malaysia |
| language | English |
| last_indexed | 2024-09-25T03:39:58Z |
| publishDate | 2023 |
| publisher | Aerospace Society Malaysia |
| record_format | dspace |
| spelling | upm.eprints-1075832024-08-19T01:50:07Z http://psasir.upm.edu.my/id/eprint/107583/ Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number Mowhoub, Mohamed Abdullah, Ermira Junita The instability of flapping wing aircrafts makes them difficult to control. As it is challenging to control and puts passengers at risk, it is not currently employed in modern aircraft technology. This study aims to analyze the aerodynamic coefficients of flapping wing aircraft at different flapping angles in order to understand their effects on the aircrafts stability. XFLR5 software was used to calculate the aerodynamics coefficients and longitudinal derivatives in different range of flapping angles from 40° to -40°. This range of flapping angles has been selected for the purpose of this study based on the physical limitations of a mechanical vehicle. Theoretically, an aircraft without a tail is unstable because the main function of a tail is to produce a moment that counters the moment produced by the wings to balance the aircraft. In the presented research, a model has been designed with and without tail, and modeled using XFLR5 to produce the aerodynamics coefficients. Then, MATLAB software was used to develop the longitudinal flight dynamics for the model. The results show that the longitudinal motion is stable for the range of flapping angle between 40° to -40°. The natural frequency increases as flapping angle changes from 0° to 40° and from 0° to -40°. In the meantime, for the short period modes eigenvalue, the real part moves toward the origin as the flapping angle changes from 0° to 40° and from 0° to -40°. On the other hand, for the phugoid modes eigenvalue, the real part moves away from the origin to the left half plane as the flapping angle changes from 0° to 40° and from 0° to -40°. Aerospace Society Malaysia 2023 Article PeerReviewed text en http://psasir.upm.edu.my/id/eprint/107583/1/107583.pdf Mowhoub, Mohamed and Abdullah, Ermira Junita (2023) Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number. Journal of Aerospace Society Malaysia, 1 (1). pp. 7-16. ISSN 3009-0520 https://www.aerosmalaysia.my/aeros_journal/index.php/journal/article/view/4 |
| spellingShingle | Mowhoub, Mohamed Abdullah, Ermira Junita Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title | Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title_full | Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title_fullStr | Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title_full_unstemmed | Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title_short | Effects of flapping wing micro air vehicle's pitching angle on stability at low reynolds number |
| title_sort | effects of flapping wing micro air vehicle s pitching angle on stability at low reynolds number |
| url | http://psasir.upm.edu.my/id/eprint/107583/1/107583.pdf |
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