| dc.creator |
Stevenson, T. N. |
|
| dc.date |
2014-11-25T15:57:24Z |
|
| dc.date |
2014-11-25T15:57:24Z |
|
| dc.date |
1961-01 |
|
| dc.date.accessioned |
2022-05-09T10:17:27Z |
|
| dc.date.available |
2022-05-09T10:17:27Z |
|
| dc.identifier |
http://dspace.lib.cranfield.ac.uk/handle/1826/8812 |
|
| dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/4812 |
|
| dc.description |
The steady incompressible laminar boundary layer equations for a
perfect gas with arbitrary distributions of wall temperature, main
stream velocity and normal velocity at the wall are solved approximately
by a method similar to that of Lighthill (1950). Equations for the skin
friction and the rate of heat transfer are obtained.
In order to assess the accuracy of these equations, solutions are
presented and compared with exact solutions for wedge type flow with
a wall temperature distribution such that the difference between the wall
and the stream temperatures is proportional to a power of the distance
from the leading edge. A Prandtl number of 0 7 is used. A solution
for the skin friction with a constant normal velocity at the wall and
constant main stream velocity is also presented.
The method is probably accurate enough for engineering purposes
in regions of negative pressure gradient.
A solution for compressible flow using a similar method is outlined. |
|
| dc.language |
en |
|
| dc.publisher |
College of Aeronautics |
|
| dc.relation |
College of Aeronautics Reports |
|
| dc.relation |
145 |
|
| dc.relation |
COA/145 |
|
| dc.title |
The laminar boundary layer with injection through a permeable wall |
|
| dc.type |
Report |
|