Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"

The first phase of this paper is aimed to develop a standard test procedure for short-duration hypersonic test facility that build at the Universiti Tenaga Nasional "UNITEN" in Malaysia. The facility has been designed, built, and commissioned for different values of diaphragm pressure rati...

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Main Authors: Amir A.-F., Yusaf T., Yusoff M.Z.
Other Authors: 15750212500
Format: Conference paper
Published: 2023
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Institution: Universiti Tenaga Nasional
id my.uniten.dspace-29834
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spelling my.uniten.dspace-298342023-12-28T16:57:50Z Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification" Amir A.-F. Yusaf T. Yusoff M.Z. 15750212500 23112065900 7003976733 Gun tunnel Mach number Shock tube Shock tunnel Shock wave Calibration Diaphragms Heat flux Heat transfer Mathematical models Shock tubes Shock waves Test facilities Thermocouples Velocity measurement Gun tunnels Hypersonic test facilities Mach number Shock tunnels Hypersonic aerodynamics The first phase of this paper is aimed to develop a standard test procedure for short-duration hypersonic test facility that build at the Universiti Tenaga Nasional "UNITEN" in Malaysia. The facility has been designed, built, and commissioned for different values of diaphragm pressure ratios. A theoretical model was developed to evaluate the Mach number values as a function of diaphragm pressure ratio for different working fluids. The second phase is to run experimental tests for different operating conditions. The calculated parameters which are pressure, temperature and velocity were very comparable to the practical results. A high precision in house made thermocouple was used to measure the temperature profile during the facility operation. A numerical transient heat transfer mathematical model was developed to evaluate the heat flux from the surface temperature history. The principle of operation and the reasoning behind building such a facility are explained, and the governing equations for the shock tube are presented. Copyright � 2006 by ASME. Final 2023-12-28T08:57:50Z 2023-12-28T08:57:50Z 2006 Conference paper 2-s2.0-33845782510 https://www.scopus.com/inward/record.uri?eid=2-s2.0-33845782510&partnerID=40&md5=e65dcbf8a7dba6d5c647c9f9db958682 https://irepository.uniten.edu.my/handle/123456789/29834 2006 Scopus
institution Universiti Tenaga Nasional
building UNITEN Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Tenaga Nasional
content_source UNITEN Institutional Repository
url_provider http://dspace.uniten.edu.my/
topic Gun tunnel
Mach number
Shock tube
Shock tunnel
Shock wave
Calibration
Diaphragms
Heat flux
Heat transfer
Mathematical models
Shock tubes
Shock waves
Test facilities
Thermocouples
Velocity measurement
Gun tunnels
Hypersonic test facilities
Mach number
Shock tunnels
Hypersonic aerodynamics
spellingShingle Gun tunnel
Mach number
Shock tube
Shock tunnel
Shock wave
Calibration
Diaphragms
Heat flux
Heat transfer
Mathematical models
Shock tubes
Shock waves
Test facilities
Thermocouples
Velocity measurement
Gun tunnels
Hypersonic test facilities
Mach number
Shock tunnels
Hypersonic aerodynamics
Amir A.-F.
Yusaf T.
Yusoff M.Z.
Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
description The first phase of this paper is aimed to develop a standard test procedure for short-duration hypersonic test facility that build at the Universiti Tenaga Nasional "UNITEN" in Malaysia. The facility has been designed, built, and commissioned for different values of diaphragm pressure ratios. A theoretical model was developed to evaluate the Mach number values as a function of diaphragm pressure ratio for different working fluids. The second phase is to run experimental tests for different operating conditions. The calculated parameters which are pressure, temperature and velocity were very comparable to the practical results. A high precision in house made thermocouple was used to measure the temperature profile during the facility operation. A numerical transient heat transfer mathematical model was developed to evaluate the heat flux from the surface temperature history. The principle of operation and the reasoning behind building such a facility are explained, and the governing equations for the shock tube are presented. Copyright � 2006 by ASME.
author2 15750212500
author_facet 15750212500
Amir A.-F.
Yusaf T.
Yusoff M.Z.
format Conference paper
author Amir A.-F.
Yusaf T.
Yusoff M.Z.
author_sort Amir A.-F.
title Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
title_short Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
title_full Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
title_fullStr Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
title_full_unstemmed Universiti Tenaga Nasional short duration hypersonic test faciliy "calibration and verification"
title_sort universiti tenaga nasional short duration hypersonic test faciliy "calibration and verification"
publishDate 2023
_version_ 1806423504996794368