| Autor: |
Nhan T. Nguyen, Daniel Nguyen, Khanh V. Trinh, Eric B. Ting |
| Rok vydání: |
2014 |
| Předmět: |
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| Zdroj: |
55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. |
| DOI: |
10.2514/6.2014-0839 |
| Popis: |
This paper presents an aeroelastic method for predicting flutter characteristics of a flexible wing transport aircraft. The aircraft model is based on NASA Generic Transport Model (GTM) with representative mass and stiffness properties to achieve a wing tip deflection about twice that of a conventional transport aircraft (10% versus 5%). This flexible wing transport aircraft is referred to as an Elastically Shaped Aircraft Concept (ESAC) which is equipped with a new type of aerodynamic control surfaces for active wing shaping control for drag reduction. This aerodynamic surface is referred to as a Variable Camber Continuous Trailing Edge Flap (VCCTEF). A vortex-lattice aerodynamic model is developed for coupling with the aeroelastic finite-element model via an automated geometry generation tool. This coupled model is used to compute static aeroelastic deflections and flutter solutions. The deflection information from the finite-element model is used to compute unsteady aerodynamic contributions to the aerodynamic force and moment coefficients. A flutter analysis is conducted to estimate the flutter boundary of the GTM and ESAC. A sensitivity analysis is also studied to examine the effect of relaxed stiffness on the flutter boundary. |
| Databáze: |
OpenAIRE |
| Externí odkaz: |
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