Experimental testing of an airframe integrated 3-D scramjet at true mach 10 flight conditions

Doherty, Luke J., Smart, Michael K. and Mee, David J. (2014). Experimental testing of an airframe integrated 3-D scramjet at true mach 10 flight conditions. In: AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2014, Atlanta, GA, United States, (). 16-20 June 2014. doi:10.2514/MHYTASP14

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Author Doherty, Luke J.
Smart, Michael K.
Mee, David J.
Title of paper Experimental testing of an airframe integrated 3-D scramjet at true mach 10 flight conditions
Conference name AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2014
Conference location Atlanta, GA, United States
Conference dates 16-20 June 2014
Convener American Institute of Aeronautics and Astronautics
Proceedings title AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Journal name AIAA AVIATION 2014 -19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Place of Publication Reston, VA, United States
Publisher American Institute of Aeronautics and Astronautics Inc.
Publication Year 2014
Sub-type Fully published paper
DOI 10.2514/MHYTASP14
Open Access Status
ISBN 9781624102844
Total pages 18
Collection year 2015
Abstract/Summary Free-jet experiments have been conducted in a shock tunnel at Mach 10 with a small airframe-integrated three-dimensional scramjet engine. The goal of the investigation was to examine the influence of airframe integration on the engine operation. The tests were conducted at a condition replicating flight at Mach 10.4 and a dynamic pressure of 48 kPa. The internal flowpath featured a rectangular-to-elliptical shape transition (REST) inlet designed for flight at Mach 12, an elliptical combustor with a constant area and diverging section, and a three-dimensional nozzle. This flowpath was integrated with a forebody and streamlined external geometry similar to what would be expected on a flight vehicle. Gaseous hydrogen fuel was injected either through portholes on the inlet, or a combination of inlet injection with a series of portholes behind a rearward facing step at the combustor entrance. Both fuel injection schemes produced robust combustion without the use of ignition aids. Comparison with tests of a three-times scale engine with a truncated forebody indicate that airframe integration and smaller scale led to a slightly reduced pressure rise. However, the core aspects of the engine characteristics remained unchanged.
Q-Index Code EX
Q-Index Status Provisional Code
Institutional Status UQ

Document type: Conference Paper
Collection: School of Mechanical & Mining Engineering Publications
 
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Created: Tue, 11 Nov 2014, 05:29:08 EST by System User on behalf of School of Mechanical and Mining Engineering