Research Article
Aeroelastic Optimization Design for High-Aspect-Ratio Wings with Large Deformation
Table 6
Results of nonlinear reanalysis.
| Terms | After linear optimization | Nonlinear reanalysis | Constraint conditions |
| Design objective | 1.766 kg | 1.766 kg | Minimum | Wingtip displacement | 549.9 mm | 625.96 mm | 380~550 mm | Torsion angle | 4.98° | 4.61° | ≤5° | Flutter speed | 38.4 m/s | 34.5 m/s | 36~40 m/s |
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