Measurements of Natural Turbulence During the BOLT II Flight Experiment
A Mach 6.0 flight experiment was performed to characterize the turbulent skin friction and heat flux associated with natural transition for vehicle-length Reynolds numbers up to 45 million. This boundary-layer turbulence flight, termed BOLT II, was the second in a series coordinated by the Air Force...
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Veröffentlicht in: | Journal of spacecraft and rockets 2024-09, Vol.61 (5), p.1281-1292 |
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description | A Mach 6.0 flight experiment was performed to characterize the turbulent skin friction and heat flux associated with natural transition for vehicle-length Reynolds numbers up to 45 million. This boundary-layer turbulence flight, termed BOLT II, was the second in a series coordinated by the Air Force Office of Scientific Research. Surface heat flux, skin friction, and pressure fluctuation spectra were acquired to characterize the transition process. The test geometry used concave curvature and swept leading edges to introduce a boundary layer with stationary laminar vortex streaks, competing transition mechanisms, and complex early turbulence. The analyses also showed that the spatial evolution of turbulence varied with respect to the location of the vortex heating streaks. Prominent overshoots were observed in the early turbulence within the streak. Turbulence data was collected for Reynolds numbers ReL up to 45×106. A common Rex=12×106 was identified as the start of equilibrium turbulence for the data presented. Conjugate heat transfer simulations, both laminar and turbulent, agreed well with the experimental data, including the laminar leading edge. The Reynolds analogy ratios based on the curve fits to the data, including compressibility, were generally between 0.9 and 1.0. The observed variations were likely the result of the spatial separation of the sensors and different definitions of Stanton number normalization between flight and theory. |
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Prominent overshoots were observed in the early turbulence within the streak. Turbulence data was collected for Reynolds numbers ReL up to 45×106. A common Rex=12×106 was identified as the start of equilibrium turbulence for the data presented. Conjugate heat transfer simulations, both laminar and turbulent, agreed well with the experimental data, including the laminar leading edge. The Reynolds analogy ratios based on the curve fits to the data, including compressibility, were generally between 0.9 and 1.0. The observed variations were likely the result of the spatial separation of the sensors and different definitions of Stanton number normalization between flight and theory.</description><identifier>ISSN: 0022-4650</identifier><identifier>EISSN: 1533-6794</identifier><identifier>DOI: 10.2514/1.A35868</identifier><language>eng</language><publisher>Reston: American Institute of Aeronautics and Astronautics</publisher><subject>Aerospace engineering ; Boundary layer transition ; Compressibility ; Design ; Experiments ; Flight ; Fluid flow ; Friction ; Geometry ; Heat ; Heat flux ; Laminar boundary layer ; Laminar heat transfer ; Leading edges ; Reynolds number ; Sensors ; Skin ; Skin friction ; Spatial data ; Stanton number ; Turbulence ; Turbulent flow</subject><ispartof>Journal of spacecraft and rockets, 2024-09, Vol.61 (5), p.1281-1292</ispartof><rights>This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. 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See also AIAA Rights and Permissions www.aiaa.org/randp.</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><cites>FETCH-LOGICAL-a176t-432e24ce08174e25a42119925d005343217c1798e90aa3104bcf4b5e7cd7a97b3</cites><orcidid>0000-0001-9608-6301</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925</link.rule.ids></links><search><creatorcontrib>Wirth, John M.</creatorcontrib><creatorcontrib>Bowersox, Rodney D. W.</creatorcontrib><creatorcontrib>Dufrene, Aaron T.</creatorcontrib><creatorcontrib>Wadhams, Timothy P.</creatorcontrib><title>Measurements of Natural Turbulence During the BOLT II Flight Experiment</title><title>Journal of spacecraft and rockets</title><description>A Mach 6.0 flight experiment was performed to characterize the turbulent skin friction and heat flux associated with natural transition for vehicle-length Reynolds numbers up to 45 million. This boundary-layer turbulence flight, termed BOLT II, was the second in a series coordinated by the Air Force Office of Scientific Research. Surface heat flux, skin friction, and pressure fluctuation spectra were acquired to characterize the transition process. The test geometry used concave curvature and swept leading edges to introduce a boundary layer with stationary laminar vortex streaks, competing transition mechanisms, and complex early turbulence. The analyses also showed that the spatial evolution of turbulence varied with respect to the location of the vortex heating streaks. Prominent overshoots were observed in the early turbulence within the streak. Turbulence data was collected for Reynolds numbers ReL up to 45×106. A common Rex=12×106 was identified as the start of equilibrium turbulence for the data presented. Conjugate heat transfer simulations, both laminar and turbulent, agreed well with the experimental data, including the laminar leading edge. The Reynolds analogy ratios based on the curve fits to the data, including compressibility, were generally between 0.9 and 1.0. The observed variations were likely the result of the spatial separation of the sensors and different definitions of Stanton number normalization between flight and theory.</description><subject>Aerospace engineering</subject><subject>Boundary layer transition</subject><subject>Compressibility</subject><subject>Design</subject><subject>Experiments</subject><subject>Flight</subject><subject>Fluid flow</subject><subject>Friction</subject><subject>Geometry</subject><subject>Heat</subject><subject>Heat flux</subject><subject>Laminar boundary layer</subject><subject>Laminar heat transfer</subject><subject>Leading edges</subject><subject>Reynolds number</subject><subject>Sensors</subject><subject>Skin</subject><subject>Skin friction</subject><subject>Spatial data</subject><subject>Stanton number</subject><subject>Turbulence</subject><subject>Turbulent flow</subject><issn>0022-4650</issn><issn>1533-6794</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2024</creationdate><recordtype>article</recordtype><recordid>eNplkE1Lw0AQhhdRsFbBn7AggpfUnf3IZo-1tjVQ7aWewyadtCkxqbtZ0H9vSgQPnuYwz_vM8BJyC2zCFchHmEyFSuLkjIxACRHF2shzMmKM80jGil2SK-8PjEGcxGZElq9ofXD4gU3naVvSN9sFZ2u6CS4PNTYF0ufgqmZHuz3Sp_VqQ9OULupqt-_o_OuIrjplr8lFaWuPN79zTN4X883sJVqtl-lsuoos6LiLpODIZYEsAS2RKys5gDFcbRlTot-CLkCbBA2zVgCTeVHKXKEuttoanYsxuRu8R9d-BvRddmiDa_qTmQDobUwkoqceBqpwrfcOy-zYv2nddwYsO9WUQTbU1KP3A2ora_9k_7gf14FimA</recordid><startdate>202409</startdate><enddate>202409</enddate><creator>Wirth, John M.</creator><creator>Bowersox, Rodney D. 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W. ; Dufrene, Aaron T. ; Wadhams, Timothy P.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-a176t-432e24ce08174e25a42119925d005343217c1798e90aa3104bcf4b5e7cd7a97b3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2024</creationdate><topic>Aerospace engineering</topic><topic>Boundary layer transition</topic><topic>Compressibility</topic><topic>Design</topic><topic>Experiments</topic><topic>Flight</topic><topic>Fluid flow</topic><topic>Friction</topic><topic>Geometry</topic><topic>Heat</topic><topic>Heat flux</topic><topic>Laminar boundary layer</topic><topic>Laminar heat transfer</topic><topic>Leading edges</topic><topic>Reynolds number</topic><topic>Sensors</topic><topic>Skin</topic><topic>Skin friction</topic><topic>Spatial data</topic><topic>Stanton number</topic><topic>Turbulence</topic><topic>Turbulent flow</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Wirth, John M.</creatorcontrib><creatorcontrib>Bowersox, Rodney D. W.</creatorcontrib><creatorcontrib>Dufrene, Aaron T.</creatorcontrib><creatorcontrib>Wadhams, Timothy P.</creatorcontrib><collection>CrossRef</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>Aerospace Database</collection><collection>Advanced Technologies Database with Aerospace</collection><jtitle>Journal of spacecraft and rockets</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Wirth, John M.</au><au>Bowersox, Rodney D. W.</au><au>Dufrene, Aaron T.</au><au>Wadhams, Timothy P.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Measurements of Natural Turbulence During the BOLT II Flight Experiment</atitle><jtitle>Journal of spacecraft and rockets</jtitle><date>2024-09</date><risdate>2024</risdate><volume>61</volume><issue>5</issue><spage>1281</spage><epage>1292</epage><pages>1281-1292</pages><issn>0022-4650</issn><eissn>1533-6794</eissn><abstract>A Mach 6.0 flight experiment was performed to characterize the turbulent skin friction and heat flux associated with natural transition for vehicle-length Reynolds numbers up to 45 million. This boundary-layer turbulence flight, termed BOLT II, was the second in a series coordinated by the Air Force Office of Scientific Research. Surface heat flux, skin friction, and pressure fluctuation spectra were acquired to characterize the transition process. The test geometry used concave curvature and swept leading edges to introduce a boundary layer with stationary laminar vortex streaks, competing transition mechanisms, and complex early turbulence. The analyses also showed that the spatial evolution of turbulence varied with respect to the location of the vortex heating streaks. Prominent overshoots were observed in the early turbulence within the streak. Turbulence data was collected for Reynolds numbers ReL up to 45×106. A common Rex=12×106 was identified as the start of equilibrium turbulence for the data presented. Conjugate heat transfer simulations, both laminar and turbulent, agreed well with the experimental data, including the laminar leading edge. The Reynolds analogy ratios based on the curve fits to the data, including compressibility, were generally between 0.9 and 1.0. The observed variations were likely the result of the spatial separation of the sensors and different definitions of Stanton number normalization between flight and theory.</abstract><cop>Reston</cop><pub>American Institute of Aeronautics and Astronautics</pub><doi>10.2514/1.A35868</doi><tpages>12</tpages><orcidid>https://orcid.org/0000-0001-9608-6301</orcidid></addata></record> |
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subjects | Aerospace engineering Boundary layer transition Compressibility Design Experiments Flight Fluid flow Friction Geometry Heat Heat flux Laminar boundary layer Laminar heat transfer Leading edges Reynolds number Sensors Skin Skin friction Spatial data Stanton number Turbulence Turbulent flow |
title | Measurements of Natural Turbulence During the BOLT II Flight Experiment |
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