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|Document Type: ||Article|
|Title: ||Hypersonic interference heating in the vicinity of surface protuberances|
|Authors: ||Estruch-Samper, D.|
MacManus, David G.
Stollery, J. L.
Lawson, Nicholas J.
Garry, Kevin P.
|Issue Date: ||2010|
|Citation: ||D. Estruch-Samper, D. G. MacManus, J. L. Stollery, N. J. Lawson and K. P. Garry, Hypersonic interference heating in the vicinity of surface protuberances, Experiments in Fluids, Volume 49, Number 3, Pages 683-699.|
|Abstract: ||The understanding of the behaviour of the flow around surface protuberances in
hypersonic vehicles is developed and an engineering approach to predict the
location and magnitude of the highest heat transfer rates in their vicinity is
presented. To this end, an experimental investigation was performed in a
hypersonic facility at freestream Mach numbers of 8.2 and 12.3 and Reynolds
numbers ranging from Re (a)/m = 3.35 x 10(6) to Re (a)/m = 9.35 x 10(6). The
effects of protuberance geometry, boundary layer state, freestream Reynolds
number and freestream Mach numbers were assessed based on thin-film heat
transfer measurements. Further understanding of the flowfield was obtained
through oil-dot visualizations and high-speed schlieren videos. The local
interference interaction was shown to be strongly 3-D and to be dominated by the
incipient separation angle induced by the protuberance. In interactions in which
the incoming boundary layer remains unseparated upstream of the protuberance,
the highest heating occurs adjacent to the device. In interactions in which the
incoming boundary layer is fully separated ahead of the protuberance, the
highest heating generally occurs on the surface just upstream of it except for
low-deflection protuberances under low Reynolds freestream flow conditions in
which case the heat flux to the side is greater.|
|Appears in Collections:||Staff publications - School of Engineering|
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