Hot wall testing methodology for impulse facilities

Zander, F. and Morgan, R. G. and Sheikh, U. A. and Buttsworth, D. R. and Teakle, P. R. (2013) Hot wall testing methodology for impulse facilities. In: 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference (AIAA 2012), 24-28 Sep 2012, Tours, France.

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Abstract

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.


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Item Type: Conference or Workshop Item (Commonwealth Reporting Category E) (Paper)
Refereed: Yes
Item Status: Live Archive
Additional Information: © 2012 by Fabian Zander. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Content may not be reproduced, downloaded, disseminated, or transferred in any form or by any means, except with the prior written permission of AIAA, except that users may download pages or other content for their own personal use. Paper no. AIAA 2012-5953
Faculty / Department / School: Historic - Faculty of Engineering and Surveying - Department of Mechanical and Mechatronic Engineering
Date Deposited: 09 Jun 2014 22:41
Last Modified: 06 Apr 2017 05:50
Uncontrolled Keywords: scramjet; hypersonics; heating; carbon fiber models; test facilities; surface treatment; boundary layers; reentry vehicle
Fields of Research : 09 Engineering > 0915 Interdisciplinary Engineering > 091508 Turbulent Flows
09 Engineering > 0901 Aerospace Engineering > 090108 Satellite, Space Vehicle and Missile Design and Testing
09 Engineering > 0901 Aerospace Engineering > 090107 Hypersonic Propulsion and Hypersonic Aerodynamics
Socio-Economic Objective: B Economic Development > 86 Manufacturing > 8613 Transport Equipment > 861301 Aerospace Equipment
Identification Number or DOI: 10.2514/6.2012-5953
URI: http://eprints.usq.edu.au/id/eprint/23917

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