{"id":{"repo_id":"uiuc","oai_identifier":"oai:www.ideals.illinois.edu:2142/20229"},"canonical_url":"https://search.dev.ndltd.org/etd/uiuc/oai:www.ideals.illinois.edu:2142/20229","repository":{"repo_id":"uiuc","name":"University of Illinois - Urbana-Champaign","base_url":"https://www.ideals.illinois.edu/oai-pmh"},"display":{"title":"Numerical calculations for flows past an unconventional airfoil","abstract":"A computer program has been developed for both two-dimensional compressible and incompressible turbulent flows around airfoils. Numerical solutions have been obtained by solving the steady-state Reynolds-averaged Navier-Stokes equations in primitive variable form. The standard k-$\\varepsilon$ turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the discretized transport equations were solved either by a hybrid or a second-order upwind differencing scheme. A multiple pressure correction procedure with implicit density treatment has been used. The solutions were obtained through an under-relaxed iterative process.","abstract_html":"A computer program has been developed for both two-dimensional compressible and incompressible turbulent flows around airfoils. Numerical solutions have been obtained by solving the steady-state Reynolds-averaged Navier-Stokes equations in primitive variable form. The standard k-$\\varepsilon$ turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the discretized transport equations were solved either by a hybrid or a second-order upwind differencing scheme. A multiple pressure correction procedure with implicit density treatment has been used. The solutions were obtained through an under-relaxed iterative process.","abstract_has_math":true,"creators":["Tsai, Ping-Ho"],"institution":"University of Illinois at Urbana-Champaign","degree_name":"Ph.D.","degree_level":"Dissertation","degree_discipline":"Mechanical Science and Engineering","degree_department":null,"school":null,"contributors":["Addy, A.L."],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2011,"date_issued":"2011-05-07T12:32:58Z","date_published":"2011-05-07T12:32:58Z","updated_at":"2026-07-22T22:25:15Z","subjects":["Engineering, Mechanical"],"languages":["eng"],"rights":["Copyright 1990 Tsai, Ping-Ho"],"rights_urls":[],"identifier_entries":[{"key":"dc:identifier","label":"Identifier","values":["AAI9021770","(UMI)AAI9021770"],"render_values":[{"text":"AAI9021770","href":null,"code":true},{"text":"(UMI)AAI9021770","href":null,"code":true}]}]},"links":{"outbound_url":"http://hdl.handle.net/2142/20229","outbound_label":"Handle","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor","label":"Contributor","values":["Addy, A.L."]},{"key":"dc:creator","label":"Author","values":["Tsai, Ping-Ho"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["2011-05-07T12:32:58Z","10000-01-01","1990"]},{"key":"dc:type","label":"Dc Type","values":["text"]},{"key":"thesis:degree_discipline","label":"Discipline","values":["Mechanical Science and Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Dissertation"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Ph.D."]},{"key":"thesis:institution_name","label":"Thesis Institution Name","values":["University of Illinois at Urbana-Champaign"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["Engineering, Mechanical"]}]},{"id":"language_rights","label":"Language and Rights","entries":[{"key":"dc:language","label":"Dc Language","values":["eng"]},{"key":"dc:rights","label":"Dc Rights","values":["Copyright 1990 Tsai, Ping-Ho"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["AAI9021770","(UMI)AAI9021770","http://hdl.handle.net/2142/20229"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description","label":"Description","values":["A computer program has been developed for both two-dimensional compressible and incompressible turbulent flows around airfoils. Numerical solutions have been obtained by solving the steady-state Reynolds-averaged Navier-Stokes equations in primitive variable form. The standard k-$\\varepsilon$ turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the discretized transport equations were solved either by a hybrid or a second-order upwind differencing scheme. A multiple pressure correction procedure with implicit density treatment has been used. The solutions were obtained through an under-relaxed iterative process.","Various cases of flow past NACA 0012 and 4412 airfoils were examined first. The experimental data available included cases with freestream Mach numbers varying from 0 to 0.799, the chord Reynolds number up to 9 $\\times$ 10$\\sp6$, and the angle of attack ranging from 0$\\sp\\circ$ to 13.87$\\sp\\circ$. The results were good when compared with experimental data. Many cases of incompressible and compressible flows past an unconventional airfoil were then computed. The freestream Mach number varied from 0 to 0.9 with the chord Reynolds number of 3.9 $\\times$ 10$\\sp6$. The general behavior of the unconventional airfoil is presented.","Made available in DSpace on 2011-05-07T12:32:58Z (GMT). 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Numerical solutions have been obtained by solving the steady-state Reynolds-averaged Navier-Stokes equations in primitive variable form. The standard k-$\\varepsilon$ turbulence model was employed and a compression turbulence model was also discussed. Based on a non-staggered arrangement on a body-fitted grid system, the discretized transport equations were solved either by a hybrid or a second-order upwind differencing scheme. A multiple pressure correction procedure with implicit density treatment has been used. The solutions were obtained through an under-relaxed iterative process.","Various cases of flow past NACA 0012 and 4412 airfoils were examined first. The experimental data available included cases with freestream Mach numbers varying from 0 to 0.799, the chord Reynolds number up to 9 $\\times$ 10$\\sp6$, and the angle of attack ranging from 0$\\sp\\circ$ to 13.87$\\sp\\circ$. The results were good when compared with experimental data. Many cases of incompressible and compressible flows past an unconventional airfoil were then computed. The freestream Mach number varied from 0 to 0.9 with the chord Reynolds number of 3.9 $\\times$ 10$\\sp6$. The general behavior of the unconventional airfoil is presented.","Made available in DSpace on 2011-05-07T12:32:58Z (GMT). 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