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Effect of Cooling on Boundary-Layer Stability at Mach Number 3

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dc.contributor.author Mack, L. en_US
dc.date.accessioned 2004-10-06T17:35:10Z
dc.date.available 2004-10-06T17:35:10Z
dc.date.issued 1992 en_US
dc.identifier.citation N/A en_US
dc.identifier.clearanceno 92-1980
dc.identifier.uri http://hdl.handle.net/2014/36709
dc.description.abstract This paper describes the calculation of the effect of wall cooling on the instability of a two-dimensional, flat-plate supersonic boundary layer under stratospheric flight conditions at Mach 3 using both the inviscid and viscous linear stability theories. en_US
dc.language.iso en_US
dc.subject.other wall cooling supersonic boundary layer stratospheric flight conditions en_US
dc.title Effect of Cooling on Boundary-Layer Stability at Mach Number 3 en_US


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