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Boundary‐Layer Transition on a Cooled Rough Sphere in Hypersonic Flow
dc.contributor.authorKuethe, Arnold M.en_US
dc.contributor.authorIshii, Takaoen_US
dc.contributor.authorAmick, James L.en_US
dc.date.accessioned2010-05-06T22:22:14Z
dc.date.available2010-05-06T22:22:14Z
dc.date.issued1964-08en_US
dc.identifier.citationKuethe, Arnold M.; Ishii, Takao; Amick, James L. (1964). "Boundary‐Layer Transition on a Cooled Rough Sphere in Hypersonic Flow." Physics of Fluids 7(8): 1198-1200. <http://hdl.handle.net/2027.42/70571>en_US
dc.identifier.urihttps://hdl.handle.net/2027.42/70571
dc.description.abstractMeasurements are given of the combined effects of two‐dimensional roughness and surface cooling on boundary layer transition at 45° from the stagnation point on a sphere in simulated hypersonic flow. With the roughness elements at 22.5° the combined effects of roughness and cooling are represented by a single functional relation between the transition length Reynolds number and the ratio between roughness height and the displacement thickness of the boundary layer at the roughness position. The measurements cover a range of ratios of surface‐to‐stagnation temperature of 0.5 to 1.0 and roughness heights of 1.8 × 10−4 to 4 × 10−3 in. Comparisons are made with measurements in incompressible flow and with one datum point in hypersonic flow.en_US
dc.format.extent3102 bytes
dc.format.extent251541 bytes
dc.format.mimetypetext/plain
dc.format.mimetypeapplication/pdf
dc.publisherThe American Institute of Physicsen_US
dc.rights© The American Institute of Physicsen_US
dc.titleBoundary‐Layer Transition on a Cooled Rough Sphere in Hypersonic Flowen_US
dc.typeArticleen_US
dc.subject.hlbsecondlevelPhysicsen_US
dc.subject.hlbtoplevelScienceen_US
dc.description.peerreviewedPeer Revieweden_US
dc.contributor.affiliationumThe University of Michigan, Ann Arbor, Michiganen_US
dc.description.bitstreamurlhttp://deepblue.lib.umich.edu/bitstream/2027.42/70571/2/PFLDAS-7-8-1198-1.pdf
dc.identifier.doi10.1063/1.1711361en_US
dc.identifier.sourcePhysics of Fluidsen_US
dc.identifier.citedreferenceR. Dunlap and A. M. Kuethe, J. Aerospace Sci. 29, 1454 (1962).en_US
dc.identifier.citedreferenceK. F. Stetson, J. Aerospace Sci. 27, 81 (1960).en_US
dc.identifier.citedreferenceR. Dunlap, J. Aerospace Sci. 29, 757 (1962).en_US
dc.identifier.citedreferenceD. R. Chapman, D. M. Kuehn, and H. K. Larson, NACA Rept. 1356 (1958).en_US
dc.identifier.citedreferenceH. L. Dryden, High Speed Aerodynamics and Jet Propulsion (Princeton University Press, Princeton. New Jersey, 1959), Division A, Vol. 5.en_US
dc.identifier.citedreferenceCalculations based on the theory of C. B. Cohen and E. Reshotko [NACA Reports 1203 and 1294 (1956)] show that for temperature ratios less than about 0.1 the displacement thickness of the boundary layer is negative.en_US
dc.identifier.citedreferenceE. R. VanDriest and J. C. Boison, J. Aerospace Sci. 24, 885 (1957).en_US
dc.identifier.citedreferenceJ. B. Peterson, Jr., and E. A. Horton, NASA Memo 2‐8‐59L (1959).en_US
dc.owningcollnamePhysics, Department of


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