The stability of stagnation point flow has long been recognized as an important problem in aerodynamic analysis. Boundary layer disturbances located near the stagnation line can have a significant effect on the overall properties of an airfoil. One example of current interest is the analysis of unsteady multi-phase stagnation flows for application to problems involving aircraft icing. In this study, numerical methods which can be used to address the stability and non-parallel unsteady development of such stagnation point problems are investigated for linearized single phase aerodynamic flows using both two-dimensional and three-dimensional methods. A streamfunction-vorticity formulation is evaluated for two-dimensional linearized stagnation flows. In addition, a primitive variable formulation is developed for three-dimensional linearized stagnation flows. The two methods are tested for grid refinement, and results obtained using the three-dimensional method are compared with those from the two-dimensional method. As expected, it is found that three-dimensional disturbances decay at a faster rate than two-dimensional ones.
","abstract_html":"<p>The stability of stagnation point flow has long been recognized as an important problem in aerodynamic analysis. Boundary layer disturbances located near the stagnation line can have a significant effect on the overall properties of an airfoil. One example of current interest is the analysis of unsteady multi-phase stagnation flows for application to problems involving aircraft icing. In this study, numerical methods which can be used to address the stability and non-parallel unsteady development of such stagnation point problems are investigated for linearized single phase aerodynamic flows using both two-dimensional and three-dimensional methods. A streamfunction-vorticity formulation is evaluated for two-dimensional linearized stagnation flows. In addition, a primitive variable formulation is developed for three-dimensional linearized stagnation flows. The two methods are tested for grid refinement, and results obtained using the three-dimensional method are compared with those from the two-dimensional method. As expected, it is found that three-dimensional disturbances decay at a faster rate than two-dimensional ones.</p>","abstract_has_math":false,"creators":["Rider, Benjamin"],"institution":null,"degree_name":"Master of Science","degree_level":"thesis","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2006,"date_issued":"2006-01-01","date_published":"2006-01-01","updated_at":"2026-07-24T02:39:30Z","subjects":[],"languages":["en"],"rights":[],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["archive/lib.dr.iastate.edu/rtd/19033/"],"render_values":[{"text":"archive/lib.dr.iastate.edu/rtd/19033/","href":null,"code":true}]}]},"links":{"outbound_url":"https://dr.lib.iastate.edu/handle/20.500.12876/72999","outbound_label":"Repository record","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["Rider, Benjamin"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2019-12-13T03:26:18.000"]},{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2020-06-30T08:12:33Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2020-06-30T08:12:33Z"]},{"key":"dc:date.issued","label":"Date","values":["2006-01-01"]},{"key":"dc:type","label":"Dc Type","values":["thesis"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["thesis"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language.iso","label":"Language (ISO)","values":["en"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["archive/lib.dr.iastate.edu/rtd/19033/"]},{"key":"dc:identifier.uri","label":"Identifier URI","values":["https://dr.lib.iastate.edu/handle/20.500.12876/72999"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["The stability of stagnation point flow has long been recognized as an important problem in aerodynamic analysis. Boundary layer disturbances located near the stagnation line can have a significant effect on the overall properties of an airfoil. One example of current interest is the analysis of unsteady multi-phase stagnation flows for application to problems involving aircraft icing. In this study, numerical methods which can be used to address the stability and non-parallel unsteady development of such stagnation point problems are investigated for linearized single phase aerodynamic flows using both two-dimensional and three-dimensional methods. A streamfunction-vorticity formulation is evaluated for two-dimensional linearized stagnation flows. In addition, a primitive variable formulation is developed for three-dimensional linearized stagnation flows. The two methods are tested for grid refinement, and results obtained using the three-dimensional method are compared with those from the two-dimensional method. As expected, it is found that three-dimensional disturbances decay at a faster rate than two-dimensional ones.
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