International Journal of Aerospace Engineering / 2016 / Article / Tab 4

Research Article

Aeroelastic Analysis of Wings in the Transonic Regime: Planform’s Influence on the Dynamic Instability

Table 4

Results of modal analysis: Case (no fictitious moments of inertia were added to finite element models).

Swept wingCurved wing

First bending mode: Case 1.058 Hz
Mode N. 1
0.916 Hz
Mode N. 1
First torsion mode: Case 12.633 Hz
Mode N. 8
12.733 Hz
Mode N. 9