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 nonuniform temperature distribution and geometrical scales using simple analytical pointwise models. Subsequently, a new, two-pronged approach to aerothermoelastic scaling is presented. It combines the classical scaling 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 classical 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.
Aerothermoelastic Scaling Laws for Hypersonic Skin Panel Configurations with Arbitrary Flow Orientation
AIAA Journal ; 57 , 10 ; 4377-4392
2019-01-22
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2018
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