Application of a partitioned field approach to transient aerothermal problems in rocket nozzles
type: Item
instance of: scholarly article
title: Application of a partitioned field approach to transient aerothermal problems in rocket nozzles
zbMATH Open document ID: 1391.76266
author: Y. Aharonov
published in: Computers and Fluids
publication date: 2018-06-19T00:00:00Z
Mathematics Subject Classification ID: 76G25
Mathematics Subject Classification ID: 76N15
zbMATH DE Number: 6891034
zbMATH Keywords: aerothermoelasticity
zbMATH Keywords: partitioned field approach
zbMATH Keywords: axisymmetric shells
zbMATH Keywords: rocket nozzles
describes a project that uses: ABAQUS
describes a project that uses: Spalart-Allmaras
describes a project that uses: TAU
MaRDI profile type: Publication
full work available at URL: j.compfluid.2013.06.014
OpenAlex ID: W1999876190
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DOI: 10.1016/J.COMPFLUID.2013.06.014
description: scientific article; zbMATH DE number 6891034