Separation Topology of Microramp Vortex Generator Controlled Flow at Mach Number 2.5
2015; American Institute of Aeronautics and Astronautics; Volume: 52; Issue: 6 Linguagem: Inglês
10.2514/1.c033280
ISSN1533-3868
AutoresQin Li, Yonghua Yan, Chaoqun Liu, Frank Lu,
Tópico(s)Computational Fluid Dynamics and Aerodynamics
ResumoNo AccessEngineering NoteSeparation Topology of Microramp Vortex Generator Controlled Flow at Mach Number 2.5Qin Li, Yonghua Yan, Chaoqun Liu and Frank LuQin LiDepartment of Mathematics, State Key Laboratory of Aerodynamics, Mianyang 621000, People's Republic of China, Yonghua YanDepartment of Mathematics, University of Texas at Arlington, Arlington, Texas 76019-0408, Chaoqun LiuDepartment of Mathematics, University of Texas at Arlington, Arlington, Texas 76019-0408 and Frank LuDepartment of Mathematics, University of Texas at Arlington, Arlington, Texas 76019-0408Published Online:8 Sep 2015https://doi.org/10.2514/1.C033280SectionsView Full TextPDFPDF Plus ToolsAdd to favoritesDownload citationTrack citations ShareShare onFacebookTwitterLinked InRedditEmail About References [1] Holden H. and Babinsky H., "Effect of Microvortex Generators on Separated Normal Shock/Boundary Layer Interactions," Journal of Aircraft, Vol. 44, No. 1, 2007, pp. 170–173. doi:https://doi.org/10.2514/1.22770 JAIRAM 0021-8669 LinkGoogle Scholar[2] Li Q. and Liu C., "LES for Supersonic Ramp Control Flow Using MVG at M=2.5 and Reθ=1440," 48th AIAA Aerospace Sciences Meeting, AIAA Paper 2010-0592, Jan. 2010. Google Scholar[3] Wu M. and Martin M. P., "Direct Numerical Simulation of Supersonic Turbulent Boundary Layer over a Compression Ramp," AIAA Journal, Vol. 45, No. 4, 1996, pp. 879–889. doi:https://doi.org/10.2514/1.27021 AIAJAH 0001-1452 LinkGoogle Scholar[4] Grinstein F. F., Margolin L. G. and Rider W. J., Implicit Large Eddy Simulation, Cambridge Univ. Press, New York, 2007, pp. 94–129. CrossrefGoogle Scholar[5] Li Q. and Liu C., "Declining Angle Effects of the Trailing Edge of a Microramp Vortex Generator," Journal of Aircraft, Vol. 47, No. 6, 2011, pp. 2086–2095; JAIRAM 0021-8669 also 48th AIAA Aerospace Sciences Meeting, AIAA Paper 2010-0714, Jan. 2010. LinkGoogle Scholar[6] Liu C. and Chen L., "Study of Mechanism of Ring-Like Vortex Formation in Late Flow Transition," 48th AIAA Aerospace Sciences Meeting, AIAA Paper 2010-1456, Jan. 2010. LinkGoogle Scholar[7] Ford C. and Babinsky H., "Micro-Ramp Control for Oblique Shock Wave/Boundary Layer Interactions," 37th AIAA Fluid Dynamics Conference and Exhibit, AIAA Paper 2007-4155, June 2007. LinkGoogle Scholar[8] Lu F., Pierce A. and Shih Y., "Experimental Study of Near Wake of Micro Vortex Generators in Supersonic Flow," 40th Fluid Dynamics Conference and Exhibit, AIAA Paper 2010-4623, 2010. LinkGoogle Scholar Previous article Next article
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