| dc.creator |
Busing, J. R. |
|
| dc.creator |
Lilley, G. M. |
|
| dc.date |
2016-12-20T09:19:22Z |
|
| dc.date |
2016-12-20T09:19:22Z |
|
| dc.date |
1955-04 |
|
| dc.date.accessioned |
2022-05-09T10:07:03Z |
|
| dc.date.available |
2022-05-09T10:07:03Z |
|
| dc.identifier |
http://dspace.lib.cranfield.ac.uk/handle/1826/11165 |
|
| dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4403 |
|
| dc.description |
Results are presented of visual tests, by surface flow
and Schlieren techniques, of the flaw over a particular wing body
combination at M = 2.0, made in the 9in x 9in supersonic wind
tunnel at the College of Aeronautics. It should be noted that
the photographs in this report represent only a small part of all
the data collected.
The effects of providing roughened bands and air jets
for transition fixation on the body are discussed. It is shown
that although such methods may be satisfactory at zero or low
angles of incidence they do not fix transition uniformly over the
complete body circumference at higher incidences. For this
reason the main part of the tests have been performed with free
transition.
The formation of vortex sheets on both wings and body
is discussed for a range of incidence and roll angles and some
conclusions are drawn as to the shape of the vortex pattern and
its induced flow effects. |
|
| dc.language |
en |
|
| dc.publisher |
College of Aeronautics |
|
| dc.relation |
CoA/N-24 |
|
| dc.relation |
24 |
|
| dc.title |
A preliminary investigation of the flow over a particular wing body combination at Mach number 2 |
|
| dc.type |
Report |
|