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Sensors 2014, 14(4), 6606-6632; doi:10.3390/s140406606

Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator

1
Faculty of Engineering, National Defence University of Malaysia, Kem Sungai Besi, Kuala Lumpur 57000, Malaysia
2
School of Engineering, University of Glasgow, James Watt South Building, Glasgow G12 8QQ, Scotland
*
Author to whom correspondence should be addressed.
Received: 14 November 2013 / Revised: 28 March 2014 / Accepted: 2 April 2014 / Published: 9 April 2014
(This article belongs to the Section Physical Sensors)

Abstract

Scramjets have become a main focus of study for many researchers, due to their application as propulsive devices in hypersonic flight. This entails a detailed understanding of the fluid mechanics involved to be able to design and operate these engines with maximum efficiency even at their off-design conditions. It is the objective of the present cold-flow investigation to study and analyse experimentally the mechanics of the fluid structures encountered within a generic scramjet inlet at M = 5. Traditionally, researchers have to rely on stream-thrust analysis, which requires the complex setup of a mass flow meter, a force balance and a heat transducer in order to measure inlet-isolator performance. Alternatively, the pitot rake could be positioned at inlet-isolator exit plane, but this method is intrusive to the flow, and the number of pitot tubes is limited by the model size constraint. Thus, this urgent need for a better flow diagnostics method is addressed in this paper. Pressure-sensitive paint (PSP) has been applied to investigate the flow characteristics on the compression ramp, isolator surface and isolator sidewall. Numerous shock-shock interactions, corner and shoulder separation regions, as well as shock trains were captured by the luminescent system. The performance of the scramjet inlet-isolator has been shown to improve when operated in a modest angle of attack. View Full-Text
Keywords: scramjet inlet; hypersonic; pressure-sensitive paint (PSP); stream-thrust scramjet inlet; hypersonic; pressure-sensitive paint (PSP); stream-thrust
This is an open access article distributed under the Creative Commons Attribution License (CC BY 3.0).

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MDPI and ACS Style

Idris, A.C.; Saad, M.R.; Zare-Behtash, H.; Kontis, K. Luminescent Measurement Systems for the Investigation of a Scramjet Inlet-Isolator. Sensors 2014, 14, 6606-6632.

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