This study describes the development of an efficient aerothermoelastic computational framework and its application to the aerothermoelastic scaling law development. In the framework, a novel approach is developed for the reduced order model of the fluid solver, which accounts for non-uniform temper- ature distribution and geometrical scales using simple analytical pointwise models. Subsequently, a new, two-pronged approach to aerothermoelastic scaling is presented. It combines the classical scal- ing approach with augmentation from numerical simulations of the specific problem. This enables one to obtain useful scaling information for important quantities that cannot be treated by the classi- cal approach. Finally, the framework is applied to study the effect of flow orientation angle on panel flutter and the development of a scaling law for a hypersonic skin panel configuration.