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Characterization of Post-shock Thermal Striations on a Cone/Flare

2020; American Institute of Aeronautics and Astronautics; Volume: 58; Issue: 5 Linguagem: Inglês

10.2514/1.j059095

1533-385X

Carson L. Running, Thomas J. Juliano, Matthew P. Borg, Roger L. Kimmel,

Combustion and Detonation Processes

No AccessTechnical NotesCharacterization of Post-shock Thermal Striations on a Cone/FlareCorrections for this articleCorrection: Characterization of Post-Shock Thermal Striations on a Cone/FlareCarson L. Running, Thomas J. Juliano, Matthew P. Borg and Roger L. KimmelCarson L. RunningUniversity of Notre Dame, Notre Dame, Indiana 46556, Thomas J. JulianoUniversity of Notre Dame, Notre Dame, Indiana 46556, Matthew P. BorgU.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433 and Roger L. KimmelU.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433Published Online:27 Feb 2020https://doi.org/10.2514/1.J059095SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Anderson J., Hypersonic and High Temperature Gas Dynamics, 2nd ed., AIAA, Reston, VA, 2006, Chaps. 6–7. https://doi.org/10.2514/4.861956 LinkGoogle Scholar[2] Arnal D. and Délery J., "Laminar-Turbulent Transition and Shock Wave/Boundary Layer Interaction," the von Karman Inst., TR-RTO-EN-AVT 116, Rhode-St-Genese, Belgium, Dec. 2005. Google Scholar[3] de la Chevaleria D. A., Fonteneau A., Luca L. D. and Cardone G., "Görtler-Type Vortices in Hypersonic Flows: The Ramp Problem," Experimental Thermal and Fluid Science, Vol. 15, No. 2, 1997, pp. 69–81. https://doi.org/10.1016/S0894-1777(97)00051-4 Google Scholar[4] Dwivedi A., Sidharth G. S., Nichols J. W., Candler G. V. and Jovanovic M. 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Jewell29 December 2021Global measurements of hypersonic shock-wave/boundary-layer interactions with pressure-sensitive paint10 April 2021 | Experiments in Fluids, Vol. 62, No. 5Related articlesCorrection: Characterization of Post-Shock Thermal Striations on a Cone/Flare3 Jun 2022AIAA Journal What's Popular Volume 58, Number 5May 2020 CrossmarkInformationCopyright © 2020 by Carson L. Running. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamicsAeronautical EngineeringAeronauticsAerothermodynamicsAviationAviation SafetyBoundary LayersFlight TestFlow RegimesFluid DynamicsOblique Shock WaveShock WavesThermodynamicsThermophysics and Heat TransferVortex DynamicsWind Tunnels KeywordsBoundary Layer SeparationFlow Visualization TechniquesFreestream Mach NumberHypersonic FlowsGortler VorticesAir Force Research LaboratoryFlight TestingWind Tunnel TestsWall TemperatureFORTRANAcknowledgmentsThe authors thank Lieutenant Michael Rynders, AFRL/RQHF, for his support conducting these tests in AFRL's Mach-6 Ludwieg Tube. In addition, thanks goes out to Notre Dame undergraduate research assistants Michael Thompson for his work with the image-mapping code and Jens Rataczak for his assistance with the model wrap. This work has been cleared for public release (Case Number 88ABW-2019-4644).PDF Received25 September 2019Accepted27 January 2020Published online27 February 2020