Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule

After the retirement of the Space shuttle, space agencies around the world have turned to space return capsules for re-entry missions. During re-entry into the atmosphere, the capsule undergoes manoeuvres at extremely high speeds reaching 20 Mach and beyond. At such hypersonic conditions, several...

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Main Author: Krishna Contractor
Other Authors: Jorg Uwe Schluter
Format: Theses and Dissertations
Language:English
Published: 2016
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Online Access:http://hdl.handle.net/10356/68796
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Institution: Nanyang Technological University
Language: English
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spelling sg-ntu-dr.10356-687962023-03-11T17:16:03Z Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule Krishna Contractor Jorg Uwe Schluter School of Mechanical and Aerospace Engineering Christian Stemmer DRNTU::Engineering::Aeronautical engineering After the retirement of the Space shuttle, space agencies around the world have turned to space return capsules for re-entry missions. During re-entry into the atmosphere, the capsule undergoes manoeuvres at extremely high speeds reaching 20 Mach and beyond. At such hypersonic conditions, several flow features occur around the capsule such as, bow shocks resulting in high heat loads and pressure gradients which in tum results in dissociation and ionization of chemical molecules in air, boundary layer transition from laminar to turbulent, expansion fans and shear layers. During the design phase, the accurate prediction of these flow features is extremely crucial. Experimental verification of these cumulative effects becomes extremely difficult and with increasing budget cuts in space research, it is not the most viable option for the prediction of the effects. As an efficient alternative, several computational methods have been developed over the past 40 years to predict flow features at hypersonic conditions. The purpose of this study is to develop an optimal blocking strategy to predict the flow around a generic Apollo space-return capsule. The study uses an iterative procedure of domain size and mesh adaptions followed by steady state simulations to optimize the number of grid points as well as the number of blocks in which the domain has been split. The meshing software being used is ICEM CFD and the simulations are done with the commercially available implicit flow solvers Fluent and CFX. Master of Science (Aerospace Engineering) 2016-06-01T04:26:00Z 2016-06-01T04:26:00Z 2016 Thesis http://hdl.handle.net/10356/68796 en 66 p. application/pdf
institution Nanyang Technological University
building NTU Library
continent Asia
country Singapore
Singapore
content_provider NTU Library
collection DR-NTU
language English
topic DRNTU::Engineering::Aeronautical engineering
spellingShingle DRNTU::Engineering::Aeronautical engineering
Krishna Contractor
Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
description After the retirement of the Space shuttle, space agencies around the world have turned to space return capsules for re-entry missions. During re-entry into the atmosphere, the capsule undergoes manoeuvres at extremely high speeds reaching 20 Mach and beyond. At such hypersonic conditions, several flow features occur around the capsule such as, bow shocks resulting in high heat loads and pressure gradients which in tum results in dissociation and ionization of chemical molecules in air, boundary layer transition from laminar to turbulent, expansion fans and shear layers. During the design phase, the accurate prediction of these flow features is extremely crucial. Experimental verification of these cumulative effects becomes extremely difficult and with increasing budget cuts in space research, it is not the most viable option for the prediction of the effects. As an efficient alternative, several computational methods have been developed over the past 40 years to predict flow features at hypersonic conditions. The purpose of this study is to develop an optimal blocking strategy to predict the flow around a generic Apollo space-return capsule. The study uses an iterative procedure of domain size and mesh adaptions followed by steady state simulations to optimize the number of grid points as well as the number of blocks in which the domain has been split. The meshing software being used is ICEM CFD and the simulations are done with the commercially available implicit flow solvers Fluent and CFX.
author2 Jorg Uwe Schluter
author_facet Jorg Uwe Schluter
Krishna Contractor
format Theses and Dissertations
author Krishna Contractor
author_sort Krishna Contractor
title Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
title_short Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
title_full Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
title_fullStr Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
title_full_unstemmed Process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
title_sort process development for grid generations to simulate hypersonic flow around a generic re-entry capsule
publishDate 2016
url http://hdl.handle.net/10356/68796
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