Boundary-layer and wake investigation in supersonic flow

Show simple item record J. Lukasiewicz en_US J. K. Royle en_US 2014-10-21T15:51:48Z 2014-10-21T15:51:48Z 1948 en_US
dc.identifier.other ARC/R&M-2613 en_US
dc.description.abstract The report describes the results of traverses of the boundary-layer and wake encountered in a small supersonic tunnel at a Mach number of 2.5. The tunnel was arranged with two throats in parallel formed by two shaped walls enclosing a shaped central element. Both the laminar and turbulent boundary-layers were encountered and compared with existing experimental and theoretical results. The frictional drag of the central element as deduced from the wake traverses is in close agreement with that calculated from considerations of laminar boundary-layer growth over the surface of the element. The tests also provide information relating to the design of nozzle profiles, particularly at the point of inflexion, where the changes of pressure gradient may have a serious effect on the boundary-layer and on the velocity distribution. en_US
dc.relation.ispartofseries Aeronautical Research Council Reports & Memoranda en_US
dc.title Boundary-layer and wake investigation in supersonic flow en_US

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