Aerothermoelastic scaling laws for hypersonic skin panel configurations with arbitrary flow orientation

Daning Huang, Peretz P. Friedmann, Tomer Rokita

Research output: Contribution to journalArticle

2 Scopus citations

Abstract

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.

Original languageEnglish (US)
Pages (from-to)4377-4392
Number of pages16
JournalAIAA journal
Volume57
Issue number10
DOIs
StatePublished - 2019

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Aerothermoelastic scaling laws for hypersonic skin panel configurations with arbitrary flow orientation'. Together they form a unique fingerprint.

  • Cite this