This paper presents the problem of nonlinear aero-thermo-elastic response of cracked plate. Bending equations of two-dimensional simply supported cracked plate subjected to supersonic flow and thermal effect is derived based on classical plate theory (CPT) and Von K arm an nonlinear relations. Linear piston theory is utilized to evaluate the aerodynamic pressure with uniform temperature variations. By applying Galerkin’s method and RungeKutta scheme, the equations are solved. The effects of parameters such as flow condition, crack dimension, temperature changes, plate aspect ratio, mass ratio, static pressure on the plate stability, flutter point and limit cycle oscillation (LCO) of the plate are examined.

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