International Journal of Aerospace Engineering / 2016 / Article / Tab 5

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 wingCurved wing

First bending mode (N. 1)
(Case ; see Table 3)
1.057 Hz0.913 Hz
First torsion mode (N. 4)
(Case ; see Table 3)
3.402 Hz3.089 Hz
First bending mode (N. 1)
(Case ; see Table 3)
1.057 Hz0.914 Hz
First torsion mode (N. 5)
(Case ; see Table 3)
4.417 Hz3.729 Hz