Subsonic Transport Composite Wing Model
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A new benchmark wing model for optimization algorithm comparisons that may include flutter and divergence, aeroelastic tailoring, buckling and post buckling, vibration and natural frequency analyses is proposed. The idea behind this wing model is that the laminate design of the wing root joint is used for the entire wing structural box (upper and lower skin panels, ribs, and front and rear spars). This laminate design is sized to support all the loads that occur at the wing root. The structure is purposely over designed to provide a starting point for subsequent structural optimization. Aerodynamic and structural and fuel masses are included as load conditions. Questions and comments may be directed to Robert G. Albers, ralbers@u.washington.edu or rgalbers@comcast.net.Reference: Albers, R. G., Tuttle, M. E., and Avery, W. B., “Subsonic Transport Composite Wing Model for Optimization Studies”, Proceedings of the 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Victoria, British Columbia, Canada, AIAA, Reston, VA, September 10-12, 2008, AIAA-2008-6016. |
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| Files available for download | File description |
| Excel 2007 spreadsheet | |
| Excel 97-2003 spreadsheet | |
| SolidWorks® SP3.1 geometry file | |
| UW Wing Design.IGS | SolidWorks® SP3.1 IGES geometry file |
| ANSYS® 11.0 database file (large file: 670 MB) |
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| UW Wing Model Load Cases: ANSYS® 11.0 load case (*.s) files, *.cdb files, and *.iges files (binary) (see UW Wing Design Read Me) |
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| UW Wing Model 3.75 Only.cdb | *.iges | UW Wing Model -1.5G Only.cdb | *.iges |