{"id":{"repo_id":"calgary","oai_identifier":"oai:ucalgary.scholaris.ca:1880/113512"},"canonical_url":"https://search.dev.ndltd.org/etd/calgary/oai:ucalgary.scholaris.ca:1880/113512","repository":{"repo_id":"calgary","name":"University of Calgary","base_url":"https://ucalgary.scholaris.ca/server/oai/request"},"display":{"title":"Verification and Validation of Open-Source Simulation Tools for Supersonic Aircraft Aerodynamic Analysis","abstract":"A verification and validation analysis of two widely-used open-source compressible-flow solvers, rhoCentralFoam and SU2, is performed for several flow problems relevant to the supersonic aerodynamics of small-scale, autonomous aircraft concepts. Vehicle concepts used as research platforms to test new aerospace technologies, such as advanced propulsion systems or large sensor payloads, require major modifications to conventional, large-scale, manned, supersonic airframe design. High-fidelity numerical simulation of these concepts in academic settings often requires the use of in-house or available open-source tools instead of expensive commercial software or those with export-control restrictions. The one-dimensional shock tube problem, two-dimensional supersonic turbulent boundary layer, and three-dimensional delta wing are simulated with both solvers. The effects of flux scheme, flux limiters, and Courant-Friedrichs-Lewy (CFL) number on solution accuracy, stability, and solver speed are assessed. The solvers' limitations and their usefulness as supersonic aircraft design tools in a holistic sense are discussed.","abstract_html":"A verification and validation analysis of two widely-used open-source compressible-flow solvers, rhoCentralFoam and SU2, is performed for several flow problems relevant to the supersonic aerodynamics of small-scale, autonomous aircraft concepts. Vehicle concepts used as research platforms to test new aerospace technologies, such as advanced propulsion systems or large sensor payloads, require major modifications to conventional, large-scale, manned, supersonic airframe design. High-fidelity numerical simulation of these concepts in academic settings often requires the use of in-house or available open-source tools instead of expensive commercial software or those with export-control restrictions. The one-dimensional shock tube problem, two-dimensional supersonic turbulent boundary layer, and three-dimensional delta wing are simulated with both solvers. The effects of flux scheme, flux limiters, and Courant-Friedrichs-Lewy (CFL) number on solution accuracy, stability, and solver speed are assessed. The solvers' limitations and their usefulness as supersonic aircraft design tools in a holistic sense are discussed.","abstract_has_math":false,"creators":["Stoldt, Henry Helmut Robert"],"institution":"Schulich School of Engineering","degree_name":"Master of Science (MSc)","degree_level":null,"degree_discipline":"Engineering – Mechanical & Manufacturing","degree_department":null,"school":null,"contributors":[],"advisors":["Johansen, Craig","Artem, Korobenko"],"committee_chairs":[],"committee_members":["Cristian, Rios","Luc, Bauwens"],"year":2021,"date_issued":"2021-06-11","date_published":"2021-06-11","updated_at":"2026-07-24T01:30:42Z","subjects":["CFD","Verification and validation","Turbulence","OpenFOAM","SU2","Delta wing","Supersonic"],"languages":["eng"],"rights":["University of Calgary graduate students retain copyright ownership and moral rights for their thesis. You may use this material in any way that is permitted by the Copyright Act or through licensing that has been assigned to the document. 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Vehicle concepts used as research platforms to test new aerospace technologies, such as advanced propulsion systems or large sensor payloads, require major modifications to conventional, large-scale, manned, supersonic airframe design. High-fidelity numerical simulation of these concepts in academic settings often requires the use of in-house or available open-source tools instead of expensive commercial software or those with export-control restrictions. The one-dimensional shock tube problem, two-dimensional supersonic turbulent boundary layer, and three-dimensional delta wing are simulated with both solvers. The effects of flux scheme, flux limiters, and Courant-Friedrichs-Lewy (CFL) number on solution accuracy, stability, and solver speed are assessed. The solvers' limitations and their usefulness as supersonic aircraft design tools in a holistic sense are discussed."]},{"key":"dc:title","label":"Title","values":["Verification and Validation of Open-Source Simulation Tools for Supersonic Aircraft Aerodynamic Analysis"]}]}],"canonical_facts":{"dc:contributor.advisor":["Johansen, Craig","Artem, Korobenko"],"dc:contributor.committeemember":["Cristian, Rios","Luc, Bauwens"],"dc:creator":["Stoldt, Henry Helmut Robert"],"dc:date":["2021-11"],"dc:date.accessioned":["2021-06-21T15:16:55Z"],"dc:date.available":["2021-06-21T15:16:55Z"],"dc:date.issued":["2021-06-11"],"dc:description.abstract":["A verification and validation analysis of two widely-used open-source compressible-flow solvers, rhoCentralFoam and SU2, is performed for several flow problems relevant to the supersonic aerodynamics of small-scale, autonomous aircraft concepts. 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