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• W2891490631 abstract "No AccessTechnical NoteBoundary-Layer Control for Effective Hypersonic IntakeAlex Ruban, Viren Menezes and Sridhar BalasubramanianAlex RubanIndian Institute of Technology Bombay, Mumbai 400 076, India*Ph.D. Student, Aerospace Engineering Department.Search for more papers by this author, Viren MenezesIndian Institute of Technology Bombay, Mumbai 400 076, India†Professor, Aerospace Engineering Department; .Search for more papers by this author and Sridhar BalasubramanianIndian Institute of Technology Bombay, Mumbai 400 076, India‡Associate Professor, Mechanical Engineering Department.Search for more papers by this authorPublished Online:2 Sep 2018https://doi.org/10.2514/1.B37066SectionsRead Now ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Kim H. D., Matsuo K. and Setoguchi T., “Investigation on Onset of Shock-Induced Separation,” Shock Waves, Vol. 6, No. 5, 1996, pp. 275–286. doi:https://doi.org/10.1007/BF02535741 SHWAEN 0938-1287 CrossrefGoogle Scholar[2] Babinsky H. and Harvey J. K., Shock Wave–Boundary-Layer Interactions, Cambridge University Press, Cambridge, England, U.K., 2011, pp. 5–86. CrossrefGoogle Scholar[3] Delery J. and Dussauge J. P., “Some Physical Aspects of Shock Wave/Boundary Layer Interactions,” Shock Waves, Vol. 19, No. 2, 2009, pp. 453–468. doi:https://doi.org/10.1007/s00193-009-0220-z SHWAEN 0938-1287 CrossrefGoogle Scholar[4] Hamed A., Yeuan J. J. and Shih S. H., “Shock-Wave/Boundary-Layer Interactions with Bleed Part 1: Effect of Slot Angle,” Journal of Propulsion and Power, Vol. 11, No. 6, 1995, pp. 1231–1235. doi:https://doi.org/10.2514/3.23962 JPPOEL 0748-4658 LinkGoogle Scholar[5] Hamed A., Yeuan J. J. and Shih S. H., “Shock-Wave/Boundary-Layer Interactions with Bleed Part 2: Effect of Slot Location,” Journal of Propulsion and Power, Vol. 11, No. 6, 1995, pp. 1236–1241. doi:https://doi.org/10.2514/3.23963 JPPOEL 0748-4658 LinkGoogle Scholar[6] Slater J. W., “Improvements in Modeling 90-Degree Bleed Holes for Supersonic Inlets,” Journal of Propulsion and Power, Vol. 28, No. 4, 2012, pp. 773–781. doi:https://doi.org/10.2514/1.B34333 JPPOEL 0748-4658 LinkGoogle Scholar[7] Schulte D., Henckels A. and Neubacher R., “Manipulation of Shock/Boundary-Layer Interactions in Hypersonic Inlets,” Journal of Propulsion and Power, Vol. 17, No. 3, 2001, pp. 585–590. doi:https://doi.org/10.2514/2.5781 JPPOEL 0748-4658 LinkGoogle Scholar[8] Smith A. N., Babinsky H., Fulker J. L. and Ashill P. R., “Shock Wave/Boundary-Layer Interaction Control Using Streamwise Slots in Transonic Flows,” Journal of Aircraft, Vol. 41, No. 3, 2004, pp. 540–546. doi:https://doi.org/10.2514/1.11479 LinkGoogle Scholar[9] Zhang Y., Tan H. J., Tian F. C. and Zhuang Y., “Control of Incident Shock/Boundary-Layer Interaction by a Two-Dimensional Bump,” AIAA Journal, Vol. 52, No. 4, 2014, pp. 767–776. doi:https://doi.org/10.2514/1.J052786 AIAJAH 0001-1452 LinkGoogle Scholar[10] McCormick D. C., “Shock/Boundary-Layer Interaction Control with Vortex Generators and Passive Cavity,” AIAA Journal, Vol. 31, No. 1, 1993, pp. 91–96. doi:https://doi.org/10.2514/3.11323 AIAJAH 0001-1452 LinkGoogle Scholar[11] Babinsky H., Li Y. and Ford C. W. P., “Microramp Control of Supersonic Oblique Shock-Wave/Boundary-Layer Interactions,” AIAA Journal, Vol. 47, No. 3, 2009, pp. 668–675. doi:https://doi.org/10.2514/1.38022 AIAJAH 0001-1452 LinkGoogle Scholar[12] Delery J. M. and Bur R. S., “The Physics of Shock Wave/Boundary Layer Interaction Control: Last Lessons Learned,” European Congress on Computational Methods in Applied Sciences and Engineering, ECCOMAS, Barcelona, Spain, 2000, pp. 1–19.doi:https://doi.org/10.13140/2.1.4478.8169 Google Scholar[13] Macheret S. O., Shneider M. N. and Miles R. B., “Optimum Performance of Electron Beam Driven Magnetohydrodynamic Generators for Scramjet Inlet Control,” AIAA Journal, Vol. 45, No. 9, 2007, pp. 2157–2163. doi:https://doi.org/10.2514/1.16955 AIAJAH 0001-1452 LinkGoogle Scholar[14] Lee S. and Loth E., “Supersonic Boundary Layer Interactions with Various Micro-Vortex Generator Geometries,” AIAA Paper 2009-3712, June 2009. doi:https://doi.org/10.2514/6.2009-3712 LinkGoogle Scholar Previous article Next article FiguresReferencesRelatedDetailsCited byStudy of multiple solution phenomenon for hypersonic air inletAerospace Science and TechnologyMach 5 Performance tests of Scramjet Engine Intake Using Free-jet Type Ground Propulsion Test FacilityJournal of the Korean Society of Propulsion Engineers, Vol. 26, No. 4Numerical Investigation of Three-dimensional Scramjet Inlet Flowfield with Porous Bleed Models at Mach 5Yoonsik Park, Yongsu Kim, Bok Jik Lee and Yang Ji Lee29 December 2021Hypersonic Incident Shock-Boundary Layer Interaction Control by Wavy PatchesJournal of Aerospace Engineering, Vol. 34, No. 1 What's Popular Volume 34, Number 6November 2018 CrossmarkInformationCopyright © 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0748-4658 (print) or 1533-3876 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. TopicsAerodynamicsAeronautical EngineeringAeronauticsBoundary LayersComputational Fluid DynamicsFinite Element MethodFinite Element SoftwareFluid DynamicsFluid MechanicsMagnetohydrodynamicsOblique Shock WavePlasma PhysicsShock WavesSpace Science and TechnologyVortex Dynamics KeywordsBoundary Layer SeparationHypersonic Shock TunnelScramjet EnginesInlet RampPressure TransducersMass FlowAdverse Pressure GradientCharge Coupled DeviceVortex GeneratorsMagnetohydrodynamic EffectsPDF Received22 January 2018Accepted26 July 2018Published online2 September 2018" @default.
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