dc.contributor.author |
J. L. Wilson |
en_US |
dc.contributor.author |
L. Pennelegion |
en_US |
dc.contributor.author |
R. F. Cash |
en_US |
dc.contributor.author |
M. J. Shilling |
en_US |
dc.date.accessioned |
2014-10-21T15:49:56Z |
|
dc.date.available |
2014-10-21T15:49:56Z |
|
dc.date.issued |
1968 |
en_US |
dc.identifier.other |
ARC/R&M-3574 |
en_US |
dc.identifier.uri |
https://reports.aerade.cranfield.ac.uk/handle/1826.2/2841 |
|
dc.description.abstract |
Heat-transfer rates have been measured on a 75°58' swept delta model and a 20° wedge in a shock tunnel at a Mach number of 8.5. The delta model had a triangular cross-section which subtended an angle of 5°15' to the sharp leading edge. The local Reynolds number varied between 1.3 x 10(to the power of 5) and 2.1 x 10(to the power of 6). The heating rates obtained were in some cases only 30 per cent of that predicted by the Eckert intermediate enthalpy method. Heat-transfer measurements on the wedge, however, showed excellent agreement. The beginning of transition of the flow, as determined from the heat-transfer measurements, occurred at local Reynolds numbers down to 6.0 x 10(to the power of 5) on the ridge line of the model. A comparison of the delta model results has been made with the caret wing measurements of East and Scott and the flat-plate measurements with those of Richards. |
en_US |
dc.relation.ispartofseries |
Aeronautical Research Council Reports & Memoranda |
en_US |
dc.title |
Heat transfer and transition measurements at M = 8.5 on a delta model and a flat plate at incidence |
en_US |