Fenômeno de wing rock em placas de compósitos com acoplamento flexão-torção
Wing rock is an undesirable oscillatory phenomenon that can occur in airfoils with an increase in the angle of attack due to effects such as asymmetric vortex breakdown. This work aims to study the frequency and amplitude of wing rock oscillation in rectangular flat plates with aspect ratios (AR)...
Na minha lista:
| Autor principal: | |
|---|---|
| Outros Autores: | |
| Formato: | Dissertação |
| Idioma: | pt_BR |
| Publicado em: |
Universidade Federal do Rio Grande do Norte
|
| Assuntos: | |
| Endereço do item: | https://repositorio.ufrn.br/handle/123456789/47538 |
| Tags: |
Adicionar Tag
Sem tags, seja o primeiro a adicionar uma tag!
|
| Resumo: | Wing rock is an undesirable oscillatory phenomenon that can occur in
airfoils with an increase in the angle of attack due to effects such as asymmetric
vortex breakdown. This work aims to study the frequency and amplitude of wing
rock oscillation in rectangular flat plates with aspect ratios (AR) over the range of 2
to 4. Aluminum and unidirectional carbon fiber composite plates, with fibers oriented
at 45° with respect to the airflow direction were tested. A testing apparatus was built
consisting of a reclining table with a free-rolling mechanism and an Arduino Uno®
sensor to capture the rotations of the plates in a wind tunnel. In general, the results
of the experiments indicated a trend of increasing wing rock amplitude with
increasing aspect ratio for angles of attack equal to or greater than 10°. The wing
rock amplitudes values were smaller for one of the configurations of fiber orientation
studied, for angles of attack over the range of 10° to 20°. For the wing rock
frequency, there was no clear correlation of frequency with the aspect ratio variation
for the angles of attack and materials studied. In summary, the results of this study
suggest that the anisotropy of composite materials can be an important design
parameter to adjust elastic properties in order to reduce wing rock effects in
aeronautical structures. |
|---|