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COBEM 2017
24th ABCM International Congress of Mechanical Engineering
RESEARCH MODEL DESIGN FOR NUMERICAL-EXPERIMENTAL STUDY OF HIGH ASPECT RATIO WING AEROELASTIC RESPONSE
Submission Author:
Orlando Tomaz da Silva Neto , MG
Co-Authors:
Diego Paes de Andrade Peña, Raimundo Duarte, ROBERTO GIL ANNES DA SILVA, Orlando Tomaz da Silva Neto
Presenter: ROBERTO GIL ANNES DA SILVA
doi://10.26678/ABCM.COBEM2017.COB17-1742
Abstract
The search to improve the performance of the aircraft has lead, among other things, the increase of wing aspect ratio. As a consequence of this solutions, the wing these solutions have the consequence an increased flexibility and, in some cases, resulting in aeroelastic problems. Among all methods used to study aeroelastic responses, the use of research models is highlighted. Reseach models for wind tunnel testing is a way to test different solutions for circumventing aeroelastic problem. As an example, the use os shape memory alloy propertires such as stiffness control an pseudoelastic properties are strategies to improve aeroelastic performance. Aiming to study the flutter response of a flexible wing of high aspect ratio, this article was intended to design, construct and test a model for this purpose, using a numerical-experimental methodology suitable for testing shape memory alloy arrangements for aeroelastic control. At first, the structure was modeled in finite elements, using Nastran, to obtain the aeroelastic response through the ZONA6 method, finally these numerical results were correlated with the experimental results. The flutter condition was evaluated analyzing the damping and coupling frequency. The numerical and experimental results reveal good approximations for the flutter velocity and oscillation frequency.
Keywords
Aeroelasticity, Flutter, Wind Tunnel, flexible wing
