Integrated aerothermoelastic analysis framework with application to skin panels

Daning Huang, Tomer Rokita, Peretz P. Friedmann

Research output: Contribution to journalArticle

8 Scopus citations

Abstract

This study describes the development of an integrated aerothermoelastic computational framework. The framework consists of a Navier-Stokes aerodynamic solver based on an Automatic Differentiation flow solver code; a finite element structural solver for moderate deflection of a composite, doubly curved, shallow shell with thermal stress; and a finite element thermal solver for heat transfer in composite shallow shells with nonlinear material properties. The solvers are loosely coupled using a partitioned scheme. An analytical approach is developed to determine the time accuracy and the so-called energy accuracy of a loosely coupled scheme, which serves as a guide for designing schemes having a high convergence rate. The aeroelastic and aerothermoelastic behaviors of two-dimensional and three-dimensional panels are investigated using the computational framework. The effects of the aspect ratio and boundary-layer thickness are found to have significant influence on the critical flutter parameter and the onset time of aerothermoelastic instability.

Original languageEnglish (US)
Pages (from-to)4562-4581
Number of pages20
JournalAIAA journal
Volume56
Issue number11
DOIs
StatePublished - 2018

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Fingerprint Dive into the research topics of 'Integrated aerothermoelastic analysis framework with application to skin panels'. Together they form a unique fingerprint.

  • Cite this