Abstract
This paper is concerned with flutter instability of a novel morphing wing at low mission speeds for different morphing configurations. In view of the flexibility of the wing, it is highly desirable to determine the conditions that trigger flutter instability. Flutter boundary was predicted using the p-k method. Structural dynamics of the wing is obtained using lumped mass method and unsteady aerodynamic using the strip model is used to evaluate corresponding aerodynamic forces and moments. The results indicate that the newly designed flexible concept of the morphing wing increases the critical flutter velocity.
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