Research Article
Aeroelastic Analysis of Wings in the Transonic Regime: Planform’s Influence on the Dynamic Instability
Table 5
Results of modal analysis: Case
and Case
.
| | Swept wing | Curved wing |
| First bending mode (N. 1) (Case ; see Table 3) | 1.057 Hz | 0.913 Hz | First torsion mode (N. 4) (Case ; see Table 3) | 3.402 Hz | 3.089 Hz | First bending mode (N. 1) (Case ; see Table 3) | 1.057 Hz | 0.914 Hz | First torsion mode (N. 5) (Case ; see Table 3) | 4.417 Hz | 3.729 Hz |
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