This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for two full coverage geometries composed of cylindrical staggered holes at a compound angle of 45 degrees. These holes varied parametrically the inclination angle to be 30 and 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. Utilizing a velocity profile at the crossflow inlet produced significant differences in the results produced when compared to a uniform freestream velocity profile. The goal of this research is to use commercially available turbulence models, in an effort to provide a benchmarking effect that matches the trusted experimental data found in past experiments. From this study, out of the 7 turbulence model cases tested, it was found that the k - ω Shear Stress Transport turbulence model with no curvature correction provided the best representation of the experimental results being benchmarked.
","abstract_html":"<p>This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for two full coverage geometries composed of cylindrical staggered holes at a compound angle of 45 degrees. These holes varied parametrically the inclination angle to be 30 and 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. Utilizing a velocity profile at the crossflow inlet produced significant differences in the results produced when compared to a uniform freestream velocity profile. The goal of this research is to use commercially available turbulence models, in an effort to provide a benchmarking effect that matches the trusted experimental data found in past experiments. From this study, out of the 7 turbulence model cases tested, it was found that the k - ω Shear Stress Transport turbulence model with no curvature correction provided the best representation of the experimental results being benchmarked.</p>","abstract_has_math":false,"creators":["Martinez, Simon R."],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2015,"date_issued":"2015-04-01T07:00:00Z","date_published":"2015-04-01T07:00:00Z","updated_at":"2026-07-27T19:26:28Z","subjects":["benchmarking","adiabatic","film cooling","Aerospace Engineering"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/edt/226","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["Martinez, Simon R."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["benchmarking","adiabatic","film cooling","Aerospace Engineering"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/edt/226"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for two full coverage geometries composed of cylindrical staggered holes at a compound angle of 45 degrees. These holes varied parametrically the inclination angle to be 30 and 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. Utilizing a velocity profile at the crossflow inlet produced significant differences in the results produced when compared to a uniform freestream velocity profile. The goal of this research is to use commercially available turbulence models, in an effort to provide a benchmarking effect that matches the trusted experimental data found in past experiments. From this study, out of the 7 turbulence model cases tested, it was found that the k - ω Shear Stress Transport turbulence model with no curvature correction provided the best representation of the experimental results being benchmarked.
"]},{"key":"dc:title","label":"Title","values":["Benchmarking of Computational Models Against Experimental Data for Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays"]}]}],"canonical_facts":{"dc:creator":["Martinez, Simon R."],"dc:description.abstract":["This study aims to benchmark experimental data that tested the effects of blowing ratio, surface angle, and hole spacing for two full coverage geometries composed of cylindrical staggered holes at a compound angle of 45 degrees. These holes varied parametrically the inclination angle to be 30 and 45 degrees, while maintaining a lateral and axial spacing of 14.5 hole diameters. Within this study, the local film cooling effectiveness was obtained from 30 rows for the 14.5 diameter spacing. Utilizing a velocity profile at the crossflow inlet produced significant differences in the results produced when compared to a uniform freestream velocity profile. The goal of this research is to use commercially available turbulence models, in an effort to provide a benchmarking effect that matches the trusted experimental data found in past experiments. From this study, out of the 7 turbulence model cases tested, it was found that the k - ω Shear Stress Transport turbulence model with no curvature correction provided the best representation of the experimental results being benchmarked.
"],"dc:identifier":["https://commons.erau.edu/edt/226"],"dc:subject":["benchmarking","adiabatic","film cooling","Aerospace Engineering"],"dc:title":["Benchmarking of Computational Models Against Experimental Data for Adiabatic Film-Cooling Effectiveness for Large Spacing Compound Angle Full Coverage Film Cooling Arrays"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:26:28Z"}