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A 48 degree-of-freedom rectangular laminated thin plate finite element including the effects of thermal and aerodynamic loadings is formulated to study the buckling and supersonic flutter characteristics of thin plate structures. Interactive effects between the critical temperature difference and critical aerodynamic pressure for the plates are also studied. The element formulation is based on the classical lamination theory. The aerodynamic pressure due to supersonic potential flow is described by a two-dimensional steady supersonic theory. The element formulation and solution procedure are evaluated by comparing results of three examples with existing alternative solutions. The practical applicability is demonstrated by performing buckling and supersonic flutter analyses of laminated thin plates under various types of temperature distributions. Based on the numerical results, the effects of aspect ratio, ratio of thermal expansion coefficients, fiber orientation, type of temperature distribution, and flow angularity on these examples are discussed.

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