Inspection of supersonic flows in a CD nozzle using experimental method

In high speed flows nozzles are used to change pressure energy to kinetic energy which in turn is used to produce thrust. In a converging-diverging nozzle, flow is augmented from subsonic to sonic velocity at the throat and further expanded to supersonic velocities at the exit. In this paper, an exp...

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Main Authors:	Azami, Muhammad Hanafi, Faheem, Mohammed, Aabid, Abdul, Mokashi, Imran, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	2019
Subjects:	TL1 Motor vehicles TL500 Aeronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/74320/ http://irep.iium.edu.my/74320/ http://irep.iium.edu.my/74320/1/IJRTE%20Nozzle%20Paper.pdf http://irep.iium.edu.my/74320/7/74320_Inspection%20of%20supersonic%20flows%20in%20a%20CD%20nozzle%20using%20experimental%20method_Scopus.pdf

id	iium-74320
recordtype	eprints
spelling	iium-743202019-11-24T16:23:41Z http://irep.iium.edu.my/74320/ Inspection of supersonic flows in a CD nozzle using experimental method Azami, Muhammad Hanafi Faheem, Mohammed Aabid, Abdul Mokashi, Imran Khan, Sher Afghan TL1 Motor vehicles TL500 Aeronautics TL780 Rockets In high speed flows nozzles are used to change pressure energy to kinetic energy which in turn is used to produce thrust. In a converging-diverging nozzle, flow is augmented from subsonic to sonic velocity at the throat and further expanded to supersonic velocities at the exit. In this paper, an experimental study is performed to evaluate the supersonic flow in a CD nozzle with a suddenly expanded duct. At the base of the nozzle, the base pressure is controlled by employing tiny jets of 1 mm diameter with a circular cross-section having exit Mach number of as unity are arranged at ninety degrees at a PCD of 13 mm and 6.5 mm from the central jet axis. Obtained wall pressure distribution is shown for Mach number 2.8, and Axi-symmetric round brass duct was used to join micro-jets, an area ratio of that duct is 3.24. Tests were conducted for L/D from 10 to 1, and the level of expansion for tests considered for wall pressure data acquisition was from 3, 5, 7, 9 and 11. The results indicate that the flow field was not aggravated due to the deployment of the control. 2019-07 Article PeerReviewed application/pdf en http://irep.iium.edu.my/74320/1/IJRTE%20Nozzle%20Paper.pdf application/pdf en http://irep.iium.edu.my/74320/7/74320_Inspection%20of%20supersonic%20flows%20in%20a%20CD%20nozzle%20using%20experimental%20method_Scopus.pdf Azami, Muhammad Hanafi and Faheem, Mohammed and Aabid, Abdul and Mokashi, Imran and Khan, Sher Afghan (2019) Inspection of supersonic flows in a CD nozzle using experimental method. International Journal of Recent Technology and Engineering (IJRTE), 8 (2S3). pp. 996-999. ISSN 2277-3878 DOI : 10.35940/ijrte.B1186.0782S319
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL1 Motor vehicles TL500 Aeronautics TL780 Rockets
spellingShingle	TL1 Motor vehicles TL500 Aeronautics TL780 Rockets Azami, Muhammad Hanafi Faheem, Mohammed Aabid, Abdul Mokashi, Imran Khan, Sher Afghan Inspection of supersonic flows in a CD nozzle using experimental method
description	In high speed flows nozzles are used to change pressure energy to kinetic energy which in turn is used to produce thrust. In a converging-diverging nozzle, flow is augmented from subsonic to sonic velocity at the throat and further expanded to supersonic velocities at the exit. In this paper, an experimental study is performed to evaluate the supersonic flow in a CD nozzle with a suddenly expanded duct. At the base of the nozzle, the base pressure is controlled by employing tiny jets of 1 mm diameter with a circular cross-section having exit Mach number of as unity are arranged at ninety degrees at a PCD of 13 mm and 6.5 mm from the central jet axis. Obtained wall pressure distribution is shown for Mach number 2.8, and Axi-symmetric round brass duct was used to join micro-jets, an area ratio of that duct is 3.24. Tests were conducted for L/D from 10 to 1, and the level of expansion for tests considered for wall pressure data acquisition was from 3, 5, 7, 9 and 11. The results indicate that the flow field was not aggravated due to the deployment of the control.
format	Article
author	Azami, Muhammad Hanafi Faheem, Mohammed Aabid, Abdul Mokashi, Imran Khan, Sher Afghan
author_facet	Azami, Muhammad Hanafi Faheem, Mohammed Aabid, Abdul Mokashi, Imran Khan, Sher Afghan
author_sort	Azami, Muhammad Hanafi
title	Inspection of supersonic flows in a CD nozzle using experimental method
title_short	Inspection of supersonic flows in a CD nozzle using experimental method
title_full	Inspection of supersonic flows in a CD nozzle using experimental method
title_fullStr	Inspection of supersonic flows in a CD nozzle using experimental method
title_full_unstemmed	Inspection of supersonic flows in a CD nozzle using experimental method
title_sort	inspection of supersonic flows in a cd nozzle using experimental method
publishDate	2019
url	http://irep.iium.edu.my/74320/ http://irep.iium.edu.my/74320/ http://irep.iium.edu.my/74320/1/IJRTE%20Nozzle%20Paper.pdf http://irep.iium.edu.my/74320/7/74320_Inspection%20of%20supersonic%20flows%20in%20a%20CD%20nozzle%20using%20experimental%20method_Scopus.pdf
first_indexed	2023-09-18T21:45:17Z
last_indexed	2023-09-18T21:45:17Z
_version_	1777413408786743296

Inspection of supersonic flows in a CD nozzle using experimental method

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