| dc.creator |
Poll, D. I. A. |
|
| dc.date |
2011-11-13T23:26:27Z |
|
| dc.date |
2011-11-13T23:26:27Z |
|
| dc.date |
1978-08-01T00:00:00Z |
|
| dc.date.accessioned |
2022-05-09T10:17:15Z |
|
| dc.date.available |
2022-05-09T10:17:15Z |
|
| dc.identifier |
http://dspace.lib.cranfield.ac.uk/handle/1826/832 |
|
| dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4682 |
|
| dc.description |
The general properties of the flow at infinite swept attachment line have been
investigated theoretically and experimentally. By using the concepts of
reference temperature and Reynolds analogy it has been possible to produce a
simple, semi-empirical calculation technique for skin friction and heat transfer
rate which is valid for free stream Mach numbers up to eight both with and
without heat transfer to the body surface. A consideration of the predictions
made by this method shows that an understanding of the transition phenomenon is
particularly important and therefore the response of the incompressible
attachment line boundary layer to two-dimensional trip wires and turbulent
boundary layers generated on bounding end plates has been investigated
experimentally. A sufficiently wide range of parameters has been covered to
ensure that the results are typical of full scale flight situations and simple
prediction criteria have been derived. By re-evaluating existing data from
several different sources it has been possible to extend the validity of some of
the principal results to include flight at hypersonic speeds. In addition to the
mechanism of transition via cross instability has been studies experimentally
for incompressible flow conditions and prediction criteria which are compatible
with advanced boundary layer calculation methods, have been developed with the
aid of liner stability theory and results obtained from the re-evaluation of
several early experimental investigations. In all cases sample calculations and
the practical implications of the various predictions have been discussed. |
|
| dc.subject |
Boundary Layer Aerodynamics |
|
| dc.subject |
Hypersonic Aerodynamics |
|
| dc.subject |
Heat Transfer |
|
| dc.title |
Some aspects of the flow near a swept attachment line with particular reference
to boundary layer transition |
|
| dc.type |
Report |
|