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• W3007167218 abstract "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*Graduate Research Assistant, Department of Aerospace and Mechanical Engineering.Search for more papers by this author, Thomas J. JulianoUniversity of Notre Dame, Notre Dame, Indiana 46556†Assistant Professor, Department of Aerospace and Mechanical Engineering.Search for more papers by this author, Matthew P. BorgU.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433‡Senior Aerospace Engineer, AFRL/RQHF, 1950 5th Street. Senior Member AIAA.Search for more papers by this author and Roger L. KimmelU.S. Air Force Research Laboratory, Wright–Patterson Air Force Base, Ohio 45433§Principal Aerospace Engineer, AFRL/RQHF, 1950 5th Street. Associate Fellow AIAA.Search for more papers by this authorPublished 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. 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P. and Simeonides G., “Parametric Studies of Shock Wave/Boundary Layer Interactions over 2D Compression Corners at Mach 6,” von Kármán Inst. for Fluid Dynamics TR 181, Sint-Genesius-Rode, Belgium, Sept. 1992. Google Scholar[11] de Luca L., Cardone G., de la Chevalerie D. and Fonteneau A., “Viscous Interaction Phenomena in Hypersonic Wedge Flow,” AIAA Journal, Vol. 33, No. 12, 1995, pp. 2293–2298. https://doi.org/10.2514/3.12982 LinkGoogle Scholar[12] Roghelia A., Olivier H., Egorov I. and Chuvakhov P., “Experimental Investigation of Görtler Vortices in Hypersonic Ramp Flows,” Experiments in Fluids, Vol. 58, No. 10, 2017, p. 139. https://doi.org/10.1007/s00348-017-2422-y CrossrefGoogle Scholar[13] Leinemann M., Radespiel R., Muñoz F., Esquieu S., McKiernan G. and Schneider S. P., “Boundary Layer Transition on a Generic Model of Control Flaps in Hypersonic Flow,” AIAA Paper 2019-1908, Jan. 2019. https://doi.org/10.2514/6.2019-1908 LinkGoogle Scholar[14] Running C. L., Juliano T. J., Jewell J. S., Borg M. P. and Kimmel R. L., “Hypersonic Shock-Wave/Boundary-Layer Interactions on a Cone/Flare,” Experimental Thermal and Fluid Science, Vol. 109, Dec. 2019, Paper 109911. https://doi.org/10.1016/j.expthermflusci.2019.109911 Google Scholar[15] Kimmel R. L., Borg M. P., Jewell J. S., Lam K., Bowersox R., Srinivasan R., Fuchs S. and Mooney T., “AFRL Ludwieg Tube Initial Performance,” AIAA Paper 2017-0102, Jan. 2017. https://doi.org/10.2514/6.2017-0102 Google Scholar[16] Running C. L., Thompson M. J., Juliano T. J. and Sakaue H., “Boundary-Layer Separation Detection for a Cone at High Angle of Attack in Mach 4.5 Flow with Pressure-Sensitive Paint,” AIAA Paper 2017-3120, June 2017. LinkGoogle Scholar[17] Running C. L., Sakaue H. and Juliano T. 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Google Scholar Previous article Next article FiguresReferencesRelatedDetailsCited byHypersonic Shock-Wave/Boundary-Layer Interactions on the ROTEX-T Cone/FlareJonathan Davami, Thomas J. Juliano, Anton Scholten and Pedro Paredes19 January 2023Implementation of Self-Aligned Focusing Schlieren for Hypersonic Boundary Layer MeasurementsJonathan L. Hill, Matthew P. Borg, Elizabeth K. Benitez, Carson L. Running and Mark F. Reeder19 January 2023Boundary Layer Separation on a Hollow-Cylinder/Flare at Mach 5James A. Threadgill, Ashish Singh, Alejandro Roskelley Garcia and Jesse C. Little19 January 2023Boundary-Layer Instabilities over a Cone–Cylinder–Flare Model at Mach 6Pedro Paredes , Anton Scholten , Meelan M. Choudhari, Fei Li, Elizabeth K. Benitez and Joseph S. Jewell29 July 2022 | AIAA Journal, Vol. 60, No. 10A wrap-film technique for infrared thermography heat-transfer measurements in high-speed wind tunnelsExperimental Thermal and Fluid Science, Vol. 135Transitional shockwave/boundary layer interaction experiments in the R2Ch blowdown wind tunnel16 February 2022 | Experiments in Fluids, Vol. 63, No. 2Boundary-Layer Instabilities Over a Cone-Cylinder-Flare Model at Mach 6Pedro Paredes, Anton Scholten, Meelan M. Choudhari, Fei Li, Elizabeth K. Benitez and Joseph S. Jewell29 December 2021Streamwise Vortices from Controlled Roughnesses on a Cone-Cylinder-Flare at Mach 6Lauren N. Wagner, Steven P. Schneider and Joseph S. 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" @default.
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