dc.contributor.author |
J. L. Fulker |
en_US |
dc.date.accessioned |
2014-10-21T15:51:35Z |
|
dc.date.available |
2014-10-21T15:51:35Z |
|
dc.date.issued |
1975 |
en_US |
dc.identifier.other |
ARC/R&M-3820 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/3102 |
|
dc.description.abstract |
Part I compares the experimentally determined aerodynamic characteristics of two 10½% thick supercritical aerofoil sections, RAE(NPL)9515 and 9530, over the Mach number range 0.3 to 0.88 and angles of incidence from -0.82° to 14°. The results are compared with the limited published results for aerofoils of a similar type. Part II presents corresponding results for RAE 9550, a 12.2% thick super- critical aerofoil derived from an NLR shockless lifting aerofoil, tested over the Mach number range 0.4 to 0.82 and angles of incidence from 1° to 11°. The results are compared with theory and with the limited published results for an aerofoil of a similar type. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Aerodynamic Data for Three Supercritical Aerofoils, RAE(NPL)9515 AND 9530, AND RAE 9550. Parts I and II |
en_US |