The stability of the infinite series of thin elastic rectangular plates simply supported along all edges and exposed to a supersonic flow is investigated. The nonzero flow yaw angle with supersonic leading edge is considered. To derive expression for the unsteady aerodynamic pressure distribution over the oscillating plate, potential flow theory was used, and an integrodifferential eigenvalue problem for finding complex eigenvalues was obtained. Flutter boundaries for the first and second modes are computed. Changing of the single-mode and coupled-mode flutter boundaries with the change of the yaw angle was shown. While they are smooth at zero angle, the boundaries become irregular, and additional isolated regions of stability and instability appear when increasing the yaw angle. This irregularity occurs due to the interaction of multiple spanwise modes, which takes place at nonzero yaw angle due to their aerodynamic coupling.
Effect of Yaw Angle on Flutter of Rectangular Plates at Low Supersonic Speeds
AIAA Journal ; 60 , 7 ; 4256-4266
2022-02-28
11 pages
Article (Journal)
Electronic Resource
English
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