NONLINEAR AEROTHERMOELASTIC BEHAVIOR OF SKIN PANEL WITH WALL SHEAR STRESS EFFECT

ABSTRACT

This paper addresses the problem of aerothermoelastic behavior of a flat skin panel with wall shear stress effect in high supersonic flow. A fully coupled high-supersonic skin panel model that accounts for all thermal–fluid–structure interactions is developed. The governing equations are based on the von Kármán large deflection of isotropic flat plates. Viscous and inviscid aerothermoelastic loading mechanisms between the fluid and structure are considered. The lumped-capacity assumption and Duhamel superposition principle are used for heat communication analysis. In addition, the effects of viscous flow shear stress, static pressure differential over the external surface, and constant axial loading in the panel middle surface have also been included in the governing equations. Using the Galerkin approach, the resulting system of differential equations is solved through the Runge–Kutta–Fehlberg integration method.

Divergence and flutter bifurcation boundaries are determined for various nondimensional parameters related to aerothermoelastic panel. Nonlinear dynamic responses of the panel for postcritical values of some selected parameters are also investigated.

Keywords:

• aerothermoelastic
• bifurcation
• nonlinear panel
• thermal conduction
• wall shear stress

Notes

*Based on Pentium III 800 computer