Journal article 505 views
Aeroelastic Stability Analysis of Tailored Pretwisted Wings
AIAA Journal, Volume: 57, Issue: 10, Pages: 4458 - 4466
Swansea University Authors: Mohammadreza Amoozgar, Michael Friswell
Full text not available from this repository: check for access using links below.
DOI (Published version): 10.2514/1.j058575
Abstract
In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unste...
| Published in: | AIAA Journal |
|---|---|
| ISSN: | 0001-1452 1533-385X |
| Published: |
American Institute of Aeronautics and Astronautics (AIAA)
2019
|
| Online Access: |
Check full text
|
| URI: | https://cronfa.swan.ac.uk/Record/cronfa53417 |
| Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
| Abstract: |
In this paper, the aeroelastic stability of a tailored aircraft wing with different pretwist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, whereas the aerodynamic loads are simulated by an incompressible unsteady aerodynamic model. The governing nonlinear partial differential equations are discretized using a time-space scheme, and the stability of the system is sought by evaluating the eigenvalues of the linearized system. The wings have linear or quadratic pretwist distributions, and the effect of various twist angles on isotropic and tailored wings is investigated. In this study, the effect of pretwist is considered on both the aerodynamic and structural models. Moreover, the effect of wing structure taper ratio in conjunction with the pretwist is investigated. The preliminary results obtained for a wing modeled as a clamped-free beam are compared with those reported in the literature and excellent agreement is observed. It is concluded that the pretwist angle leads to mode coupling and also has a significant effect on the flutter speed of the wing. By pretwisting the wing, the flutter speed of the wing with respect to the clean wing increases until a specific twist value and then decreases. Moreover, adding the pretwist to the wing decreases the flutter frequency. Finally, results highlighting the effect of bend-twist elastic coupling and wing taper ratio in combination with the pretwist angle on the aeroelastic stability of the wing are provided. |
|---|---|
| College: |
Faculty of Science and Engineering |
| Issue: |
10 |
| Start Page: |
4458 |
| End Page: |
4466 |