dc.contributor.author | J.A. Beavan et al | en_US |
dc.date.accessioned | 2014-10-21T15:52:17Z | |
dc.date.available | 2014-10-21T15:52:17Z | |
dc.date.issued | 1948 | en_US |
dc.identifier.other | ARC/R&M-2678 | en_US |
dc.identifier.uri | https://reports.aerade.cranfield.ac.uk/handle/1826.2/3221 | |
dc.description.abstract | The lift on a number of aerofoil sections mostly of 2-in. chord has been determined over a wide range of incidence and Mach number by measuring tile pressures on the walls of the 20 x 8 in. High Speed Tunnel. There is some evidence that the low Reynolds number of the tests is not important. | en_US |
dc.relation.ispartofseries | Aeronautical Research Council Reports & Memoranda | en_US |
dc.title | Measurements of maximum lift on 26 aerofoil sections at high mach number. Part I tests on 19 aerofoils. Part II Tests on a Further 7 Aerofoils | en_US |