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Development of an adaptive strand-Cartesian solver in 2D for non-equilibrium aerothermodynamics simulations

Development of an adaptive strand-Cartesian solver in 2D for non-equilibrium aerothermodynamics simulations
Development of an adaptive strand-Cartesian solver in 2D for non-equilibrium aerothermodynamics simulations
The extreme conditions experienced in hypersonic flight can be difficult to reproduce in ground test facilities. As such, the use of computational simulations is vital in the design of Thermal Protection Systems (TPSs) for hypersonic vehicles. Many TPSs use materials that ablate and this leads to changes in shape of the body with time. As such, the computational mesh needs to be updated, whilst maintaining a high resolution in the shock and boundary layer regions, which can require significant user input. In this work, a prototype strand/Cartesian Adaptive Mesh Refinement (CAMR) solver has been created using the AMROC (Adaptive Mesh Refinement in Object-oriented C++) framework, that enables meshes to be generated with minimal user input. The strand/CAMR technique combines a “strand” mesh, grown from a discretised surface, in the nearbody region with an adaptive Cartesian mesh in the off-body region in order to highly resolve off-body shocks and boundary layers. The development of the off-body and near-body two-temperature Navier-Stokes solvers, and the overset algorithms used to join the two regions, is described. A series of test cases that aim to verify and validate the hypersonic 2D/axisymmetric strand/CAMR solver are presented. An order-of-accruacy test is carried out on an overset domain to verify the implementation of the new spatial and time integration methods. A high-enthalpy experiment is simulated in order to validate the new solver and investigate the influence of the overset mesh on heat flux predictions. Finally, the automated surface deformation enabled by the new solver is demonstrated through the simulation of a recessing nose tip. The results indicate that the strand/CAMR technique can be used to accurately simulate vehicles in hypersonic flows and offers a high level of automation.
hypersonic, strand, overset
Atkins, Chay William Charles
8d81836b-91c3-4013-ba2b-8791ee0dbce1
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314
Atkins, Chay William Charles
8d81836b-91c3-4013-ba2b-8791ee0dbce1
Deiterding, Ralf
ce02244b-6651-47e3-8325-2c0a0c9c6314

Atkins, Chay William Charles and Deiterding, Ralf (2022) Development of an adaptive strand-Cartesian solver in 2D for non-equilibrium aerothermodynamics simulations. In Proc. 2nd International Conference on HighSpeed Vehicle Science & Technology. 20 pp . (In Press)

Record type: Conference or Workshop Item (Paper)

Abstract

The extreme conditions experienced in hypersonic flight can be difficult to reproduce in ground test facilities. As such, the use of computational simulations is vital in the design of Thermal Protection Systems (TPSs) for hypersonic vehicles. Many TPSs use materials that ablate and this leads to changes in shape of the body with time. As such, the computational mesh needs to be updated, whilst maintaining a high resolution in the shock and boundary layer regions, which can require significant user input. In this work, a prototype strand/Cartesian Adaptive Mesh Refinement (CAMR) solver has been created using the AMROC (Adaptive Mesh Refinement in Object-oriented C++) framework, that enables meshes to be generated with minimal user input. The strand/CAMR technique combines a “strand” mesh, grown from a discretised surface, in the nearbody region with an adaptive Cartesian mesh in the off-body region in order to highly resolve off-body shocks and boundary layers. The development of the off-body and near-body two-temperature Navier-Stokes solvers, and the overset algorithms used to join the two regions, is described. A series of test cases that aim to verify and validate the hypersonic 2D/axisymmetric strand/CAMR solver are presented. An order-of-accruacy test is carried out on an overset domain to verify the implementation of the new spatial and time integration methods. A high-enthalpy experiment is simulated in order to validate the new solver and investigate the influence of the overset mesh on heat flux predictions. Finally, the automated surface deformation enabled by the new solver is demonstrated through the simulation of a recessing nose tip. The results indicate that the strand/CAMR technique can be used to accurately simulate vehicles in hypersonic flows and offers a high level of automation.

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Accepted/In Press date: 12 September 2022
Venue - Dates: HiSST: 2nd International Conference on High-Speed Vehicle Science & Technology, , Bruges, Belgium, 2022-09-12 - 2022-09-15
Keywords: hypersonic, strand, overset

Identifiers

Local EPrints ID: 470593
URI: http://eprints.soton.ac.uk/id/eprint/470593
PURE UUID: 2fd4b552-b730-4252-92a9-62ea060e1dd8
ORCID for Chay William Charles Atkins: ORCID iD orcid.org/0000-0001-9243-4903
ORCID for Ralf Deiterding: ORCID iD orcid.org/0000-0003-4776-8183

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Date deposited: 14 Oct 2022 16:32
Last modified: 15 Oct 2022 01:47

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