dc.contributor.author | B. D. Henshall | en_US |
dc.contributor.author | R. F. Cash | en_US |
dc.date.accessioned | 2014-10-21T15:54:40Z | |
dc.date.available | 2014-10-21T15:54:40Z | |
dc.date.issued | 1957 | en_US |
dc.identifier.other | ARC/R&M-3093 | en_US |
dc.identifier.uri | https://reports.aerade.cranfield.ac.uk/handle/1826.2/3664 | |
dc.description.abstract | Direct-shadow and schlieren photographs and pressure distributions of the flow past a two-dimensional 4 per cent thick biconvex aerofoil for a limited range of incidences at Mach numbers of 1.40 and 1.63 are presented. Shock-induced boundary-layer separation at the trailing edge of the aerofoil was present at M 0 = 1.63 with transition-free boundary layers but was absent up to 5 deg incidence at M 0 = 1.68 with transition-fixed boundary layers and up to 6 deg incidence at M 0 = 1.40 with transition-free boundary layers. | en_US |
dc.relation.ispartofseries | Aeronautical Research Council Reports & Memoranda | en_US |
dc.title | Observations of the flow patterns of two-dimensional 4 per cent thick biconvex aerofoil at Mo = 1.40 and 1.63 | en_US |