{"id":{"repo_id":"nps","oai_identifier":"oai:calhoun.nps.edu:10945/39753"},"canonical_url":"https://search.dev.ndltd.org/etd/nps/oai:calhoun.nps.edu:10945/39753","repository":{"repo_id":"nps","name":"Naval Postgraduate School","base_url":"https://calhoun.nps.edu/server/oai/request"},"display":{"title":"Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades","abstract":"Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge.","abstract_html":"Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge.","abstract_has_math":false,"creators":["Wakefield, Bryce Edwin."],"institution":"Monterey, California. Naval Postgraduate School","degree_name":null,"degree_level":null,"degree_discipline":null,"degree_department":"Department of Aeronautics and Astronautics","school":null,"contributors":[],"advisors":["Hobson, Garth V."],"committee_chairs":[],"committee_members":[],"year":1993,"date_issued":"1993-12","date_published":"1993-12","updated_at":"2026-07-27T20:24:46Z","subjects":[],"languages":["en_US"],"rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://hdl.handle.net/10945/39753","outbound_label":"Handle","outbound_source":"dc:identifier.uri"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:contributor.advisor","label":"Advisor","values":["Hobson, Garth V."]},{"key":"dc:contributor.department","label":"Department","values":["Department of Aeronautics and Astronautics"]},{"key":"dc:creator","label":"Author","values":["Wakefield, Bryce Edwin."]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"dc:date","label":"Dc Date","values":["December 1993"]},{"key":"dc:date.accessioned","label":"Dc Date Accessioned","values":["2014-03-26T23:23:07Z"]},{"key":"dc:date.available","label":"Dc Date Available","values":["2014-03-26T23:23:07Z"]},{"key":"dc:date.issued","label":"Date","values":["1993-12"]},{"key":"dc:publisher","label":"Institution","values":["Monterey, California. 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Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge."]},{"key":"dc:title","label":"Title","values":["Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades"]}]}],"canonical_facts":{"dc:contributor.advisor":["Hobson, Garth V."],"dc:contributor.department":["Department of Aeronautics and Astronautics"],"dc:creator":["Wakefield, Bryce Edwin."],"dc:date":["December 1993"],"dc:date.accessioned":["2014-03-26T23:23:07Z"],"dc:date.available":["2014-03-26T23:23:07Z"],"dc:date.issued":["1993-12"],"dc:description.abstract":["Turbulence measurements near the leading edge of a compressor stator were made in a subsonic cascade wind tunnel with a hotwire system. Using a single hot-film probe, velocity and turbulence distortion data were obtained about the leading edge of the Controlled-Diffusion (CD) blades in order to verify Laser Doppler Velocimetry (LDV) data taken in earlier studies. Measurements were conducted at a Mach number of .25, a Reynolds number of 711000 and an inlet flow angle of 48 degrees. Turbulence profiles obtained in the pitch-wise direction were found to be in good agreement with previous LDV measurements. These data indicated a localized increase in turbulence around the leading edge due to the interaction of the free-shear layer with the inlet turbulence. This free-shear layer extends over the separation bubble, which forms on the suction side of the blades' leading edge."],"dc:identifier.uri":["https://hdl.handle.net/10945/39753"],"dc:language.iso":["en_US"],"dc:publisher":["Monterey, California. Naval Postgraduate School"],"dc:rights":["This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States."],"dc:title":["Hotwire measurements of the turbulent flow into a cascade of controlled-diffusion compressor blades"],"dc:type":["Thesis"]},"updated_at":"2026-07-27T20:24:46Z"}