When the structural study of an airplane wing, it is difficult to accurately model the aerodynamic forces sudden by the wing of the plane. For ease of analysis, we divided theoretical maximum lift of the wing main spar on his or her veins. These classifications mean that the entire wing is stronger than necessary and so that the structure will not be fully optimized. To overcome this problem, it should be ensured to apply a distribution of aerodynamic lift on the entire surface of the wing, it would be able to get a load distribution on the wing much more reliable. To achieve this, we need to link the results of a software calculating the aerodynamic loads of the wing with the results of software to its design and structural analysis. In this project, the software used to calculate the pressure coefficients on the wing is XFLR5 and software for the design and structural analysis will CATIA V5. The XFLR5 software allows rapid analysis of a wing based on the analysis of its profiles. This software calculates profiles of performance in the same way as XFOIL and lets you choose from three methods of computed to provide the wing performance: Lifting Line Theory (LLT) Vortex Lattice Méthod (VLM) and 3D Panels. In our methodology, we use the method for calculating 3D panels whose validity was tested in the wind tunnel to confirm the calculations on XFLR5. Regarding the design and finite element analysis of the structure, CATIA V5 is commonly used in the aerospace field. CATIA V5 provides automation of the steps of the wing designs. Thus, in this paper, we describe the methodology for the aerostructure study of an airplane wing.
| Date | 25 Nov 2015 |
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| Original language | French |
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| Awarding Institution | - École de technologie supérieure
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| Supervisor | Ruxandra Botez (Supervisor) & Henri Champliaud (Co-supervisor) |
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Communier, D. (Author),
Botez (Supervisor) &
Champliaud (Co-supervisor),
25 Nov 2015Student thesis: Master's thesis › Master in Engineering: Engineering