Hot wall testing methodology for impulse facilities

Zander, F., Morgan, R.G., Sheikh, U.A., Buttsworth, D. R. and Teakle, P. R. (2012). Hot wall testing methodology for impulse facilities. In: 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012. 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012, Tours, France, (). 24 - 28 September 2012. doi:10.2514/6.2012-5953


Author Zander, F.
Morgan, R.G.
Sheikh, U.A.
Buttsworth, D. R.
Teakle, P. R.
Title of paper Hot wall testing methodology for impulse facilities
Conference name 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Conference location Tours, France
Conference dates 24 - 28 September 2012
Proceedings title 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Place of Publication Red Hook, N.Y
Publisher Currans
Publication Year 2012
Year available 2012
Sub-type Fully published paper
DOI 10.2514/6.2012-5953
ISBN 9781600869310
9781627481823
1627481826
Total pages 6
Collection year 2013
Language eng
Abstract/Summary The design of hypersonic flight systems requires extensive ground testing to understand the flow characteristics that are important for the flight vehicle. The work presented within this paper demonstrates a new model pre-heating technique that allows models to be tested in hypersonic impulse facilities with wall temperatures in excess of 2000 K. Utilising carbon fibre models and resistive heating, this technique enables a new range of testing opportunities in these facilities. Preliminary testing has been conducted demonstrating increased surface chemistry rates with an elevated wall temperature model representative of a blunt body atmospheric entry vehicle. This methodology has enabled a range of new testing to be proposed including blunt body models investigating the effect of hot walls, ablating surfaces and surface reactions on the flow field. Additional testing targeting boundary layer physics and scramjet flow phenomena have also been proposed including investigations into transition, boundary layer development, shock interactions, boundary layer combustion, mixing and ignition lengths and radical farming. The effect of the increased wall temperature on these phenomena is of great interest for the understanding of the hypersonic flow fields.
Subjects 1912 Space and Planetary Science
2202 History and Philosophy of Specific Fields
2207 Control and Systems Engineering
Q-Index Code E1
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Conference Paper
Collections: School of Mechanical & Mining Engineering Publications
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