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International Journal of Aerospace Engineering
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International Journal of Aerospace Engineering
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2016
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Article
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Tab 4
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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 wing
Curved 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