Comparison of mach 10 scramjet measurements from different impulse facilities

McGilvray, Matthew, Kirchhartz, Rainer and Jazra, Thomas (2010) Comparison of mach 10 scramjet measurements from different impulse facilities. AIAA Journal, 48 8: 1647-1651. doi:10.2514/1.J050025


Author McGilvray, Matthew
Kirchhartz, Rainer
Jazra, Thomas
Title Comparison of mach 10 scramjet measurements from different impulse facilities
Journal name AIAA Journal   Check publisher's open access policy
ISSN 0001-1452
Publication date 2010-08-01
Sub-type Article (original research)
DOI 10.2514/1.J050025
Open Access Status Not Open Access
Volume 48
Issue 8
Start page 1647
End page 1651
Total pages 5
Place of publication Reston, VA, USA
Publisher American Institute of Aeronautics and Astronautics
Language eng
Subject 0901 Aerospace Engineering
Abstract A comparison is made between scramjet pressure data taken in two different impulse facilities, a reflected shock tunnel and an expansion tunnel, to provide verification of flow similarity. A two-dimensional hydrogen-fueled scramjet was tested in both facilities at a Mach 10, 66 kPa dynamic pressure, flight-replication condition. The entire flowfield was reproduced, including the inlet, combustor, and thrust nozzle. The expansion-tunnel model was a 40%-scaled model of that investigated in the shock tunnel, as the generated core flow was smaller. Applying density-length scaling, the density of the freestream was increased by a factor of 2.5 in the expansion tube to maintain similarity between the experimental setups. Results show agreement within the experimental uncertainty between the two data sets at similar fuel equivalence ratios, indicating the repeatability of scramjet pressure measurements, independent of the experimental facility used. It is further demonstrated that density-length scaling is appropriate for the flows generated in the investigated scramjet engines. Verification is also provided of the analysis technique used to process experimental scramjet data sets that involve transient inflow conditions. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
Keyword Engines
Scramjet engine
Q-Index Code C1
Q-Index Status Confirmed Code
Institutional Status UQ

Document type: Journal Article
Sub-type: Article (original research)
Collections: School of Mechanical & Mining Engineering Publications
Official 2011 Collection
 
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Created: Thu, 23 Sep 2010, 21:04:41 EST by Maria Campbell on behalf of School of Mechanical and Mining Engineering