Aeroelastic Stability Analysis of Tailored Pre-twisted Wings
MR Amoozgar (Swansea University), SA Fazelzadeh (Shiraz University, Iran), MI Friswell (Swansea University) & DH Hodges (Georgia Institute of Technology, USA)
AIAA Journal, Vol. 57, No. 10, October 2019, pp. 4458-4466
In this paper, the aeroelastic stability of a tailored aircraft wing with different pre-twist distributions is investigated. The structure of the wing is modeled using the geometrically exact fully intrinsic beam theory of Hodges, while 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 pre-twist distributions, and the effect of various twist angles on isotropic and tailored wings is investigated. In this study, the effect of pre-twist is considered on both the aerodynamic and structural models. Moreover, the effect of wing structure taper ratio in conjunction with the pre-twist 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 pre-twist angle leads to mode coupling and also has a significant effect on the flutter speed of the wing. By pre-twisting 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 pre-twist 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 pre-twist angle on the aeroelastic stability of the wing are provided.
This material has been published in the AIAA Journal, Vol. 57, No. 10, October 2019, pp. 4458-4466. Unfortunately the copyright agreement with AIAA does not allow for the PDF file of the paper to be available on this website. However the paper is available from AIAA - see the link below.
Link to paper using doi: 10.2514/1.J058575
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