dc.contributor.author |
E. W. E. Rogers |
en_US |
dc.contributor.author |
V. G. Quincey |
en_US |
dc.contributor.author |
J. Callinan |
en_US |
dc.date.accessioned |
2014-10-21T15:55:49Z |
|
dc.date.available |
2014-10-21T15:55:49Z |
|
dc.date.issued |
1961 |
en_US |
dc.identifier.other |
ARC/R&M-3306 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/3885 |
|
dc.description.abstract |
Pressure-plotting and strain-gauge balance tests have been made at a Mach number of 1.41 on a conically cambered cone of 30° semi-vertex angle, and with a ratio of the major to the minor axis of its cross-section equal to 11.55. The camber line was designed for a CL of 0.3 by the method of Ref. 2. The upper-surface pressure distribution was found to be strongly influenced by the boundary-layer state in the leading-edge region, and when this was turbulent good agreement with the theoretical spanwise loading was obtained at the design CL, though this was obtained at a somewhat higher incidence than the design value. The flow development with incidence for both boundary-layer states is discussed with the aid of oil-flow patterns. The results for the cambered cone are compared with those obtained in 1954 for a corresponding uncambered elliptic cone. Both cones have the same normal-force curve slope; the cambered cone has a higher minimum drag coefficient, but a smaller lift-dependent drag factor. At the design C L the drag of the two models is the same. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Experiments at M = 1.41 on a thin, conically-cambered elliptic cone of 30 degrees semi-vertex angle |
en_US |