Next Article in Journal
Advances in Bio-Tactile Sensors for Minimally Invasive Surgery Using the Fibre Bragg Grating Force Sensor Technique: A Survey
Previous Article in Journal
Uncertain Data Clustering-Based Distance Estimation in Wireless Sensor Networks
Article Menu

Export Article

Open AccessArticle
Sensors 2014, 14(4), 6606-6632; https://doi.org/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)
Full-Text   |   PDF [7339 KB, uploaded 21 June 2014]

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).
SciFeed

Share & Cite This Article

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.

Show more citation formats Show less citations formats

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Sensors EISSN 1424-8220 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top