Hot-wall reentry testing in hypersonic impulse facilities

Zander, F. and Morgan, R. G. and Sheikh, U. and Buttsworth, D. R. and Teakle, P. R. (2013) Hot-wall reentry testing in hypersonic impulse facilities. AIAA Journal, 51 (2). pp. 476-484. ISSN 0001-1452


Hypersonic testing in impulse facilities replicates various flow characteristics accurately; however, because of the short test times, some phenomena cannot be fully simulated. Previous testing has been conducted with preheated walls up to 800 K; however, this falls well short of the typical temperatures characteristic of ablators in hypervelocity
reentry (~2000 – 3000 K). The concept presented here is to use resistive heating on a carbon – carbon model to preheat the model immediately before conducting a test. This method has enabled testing at wall temperatures in excess of 2000 K in the X2 expansion tube at the University of Queensland. The model used was a short half-cylinder with a diameter-to-length ratio of 4.5 and was tested in a 8.6 km∕s Earth-entry flow monitored by ultraviolet spectrometry.
The testing campaign showed that there was a significant increase in the cyanogen formation off the surface of the model when it was heated to 2000 K. This testing demonstrates the viability of the presented method, which will enable a new range of testing to be conducted in impulse facilities with emphasis on hypervelocity flows, in particular those in which the real flight vehicle uses a carbon-based ablator as the thermal protection system.

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Item Type: Article (Commonwealth Reporting Category C)
Refereed: Yes
Item Status: Live Archive
Additional Information: © 2012 by Fabian Zander. Permanent restricted access to published version due to publisher copyright policy.
Faculty/School / Institute/Centre: Current - Faculty of Health, Engineering and Sciences - School of Mechanical and Electrical Engineering
Date Deposited: 18 Feb 2015 22:50
Last Modified: 13 Feb 2017 01:19
Uncontrolled Keywords: flight vehicles; flow characteristics; hypervelocity flow; resistive heating; thermal protection system; ultraviolet spectrometry; wall temperatures
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 > 88 Transport > 8803 Aerospace Transport > 880399 Aerospace Transport not elsewhere classified
Identification Number or DOI: 10.2514/1.J051867

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