Abstract
Next we consider the transient aeroelastic response of a wing-like structure in transonic flow. The structure is assumed to be indefinitely long so that a two-dimensional analysis can be performed. It includes a thin aluminum skin (Young modulus E = 1.3 x 10) that is stiffened with three vertical and parallel rigid shear panels. An N AC AGO 12 cross section is considered. This wing-like structure is assumed to rest on a Winkler-type foundation. The surface of the structure is discretized using two-node hermitian beam elements. Multiple moving frames of reference are invoked to follow the motion and track the deformation of the structural skin. The structure is placed in a flow at Mach number Mw = 0.8. The imposed velocity is Uw = 7.96. The angle of attack is slightly perturbed from an initial position and the response of the structure is computed. Figure 4 reports the variation of the angle of attack in time.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
