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.
Integrated Aerothermoelastic Analysis Framework with Application to Skin Panels
AIAA Journal ; 56 , 11 ; 4562-4581
2018-09-20
20 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
About the Aerothermoelastic Stability of Panels in Supersonic Flows
Tema Archiv | 2013
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