Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes

This paper presents the results of an experimental work carried out to find the wall pressure distribution in a suddenly enlarged duct. The enlarged duct is attached to the exit of a convergent- divergent axisymmetric nozzle. The area ratio (i.e. ratio between cross sectional arean of the sudden exp...

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Main Authors:	Baig, Maugal Ahmed Ali, Khan, Sher Afghan, Rathakrishnan, E.
Format:	Article
Language:	English
Published:	rspublication 2012
Subjects:	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/49921/ http://irep.iium.edu.my/49921/ http://irep.iium.edu.my/49921/1/baig_m_a_-_2012_-_experimental_investigations_on_wall_pressure-IJETED.pdf

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recordtype	eprints
spelling	iium-499212016-07-18T02:07:53Z http://irep.iium.edu.my/49921/ Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes Baig, Maugal Ahmed Ali Khan, Sher Afghan Rathakrishnan, E. TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets This paper presents the results of an experimental work carried out to find the wall pressure distribution in a suddenly enlarged duct. The enlarged duct is attached to the exit of a convergent- divergent axisymmetric nozzle. The area ratio (i.e. ratio between cross sectional arean of the sudden expansion duct and the nozzle exit area) considered in the present study is 4.84. The supersonic Mach number regimes considered in the present study are 1.87, 2.2 and 2.58. The length to diameter ratio is 4. The nozzle pressure ratio (NPR) used is 3, 5, 7, 9, and 11 for all the Mach numbers. An active control method in the form of Microjets is used to control the base pressure. The prime investigations are towards finding the effect of Microjets on wall pressure for above said parametric conditions. It is found that for area ratio 4.84 the Microjets which are used as active control method for base pressure, does not adversely affect the wall pressure,contradicting the peculiar oscillatory nature in the enlarged duct when controls are employed. rspublication 2012-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/49921/1/baig_m_a_-_2012_-_experimental_investigations_on_wall_pressure-IJETED.pdf Baig, Maugal Ahmed Ali and Khan, Sher Afghan and Rathakrishnan, E. (2012) Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes. International Journal of Emerging Trends in Engineering and Development (IJETED), 6 (2). pp. 496-504. ISSN 2249-6149 http://www.rspublication.com/ijeted/ijeted_index.htm
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics TL780 Rockets Baig, Maugal Ahmed Ali Khan, Sher Afghan Rathakrishnan, E. Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
description	This paper presents the results of an experimental work carried out to find the wall pressure distribution in a suddenly enlarged duct. The enlarged duct is attached to the exit of a convergent- divergent axisymmetric nozzle. The area ratio (i.e. ratio between cross sectional arean of the sudden expansion duct and the nozzle exit area) considered in the present study is 4.84. The supersonic Mach number regimes considered in the present study are 1.87, 2.2 and 2.58. The length to diameter ratio is 4. The nozzle pressure ratio (NPR) used is 3, 5, 7, 9, and 11 for all the Mach numbers. An active control method in the form of Microjets is used to control the base pressure. The prime investigations are towards finding the effect of Microjets on wall pressure for above said parametric conditions. It is found that for area ratio 4.84 the Microjets which are used as active control method for base pressure, does not adversely affect the wall pressure,contradicting the peculiar oscillatory nature in the enlarged duct when controls are employed.
format	Article
author	Baig, Maugal Ahmed Ali Khan, Sher Afghan Rathakrishnan, E.
author_facet	Baig, Maugal Ahmed Ali Khan, Sher Afghan Rathakrishnan, E.
author_sort	Baig, Maugal Ahmed Ali
title	Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
title_short	Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
title_full	Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
title_fullStr	Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
title_full_unstemmed	Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes
title_sort	experimental investigations on wall pressure in suddenly enlarged ducts at supersonic mach number regimes
publisher	rspublication
publishDate	2012
url	http://irep.iium.edu.my/49921/ http://irep.iium.edu.my/49921/ http://irep.iium.edu.my/49921/1/baig_m_a_-_2012_-_experimental_investigations_on_wall_pressure-IJETED.pdf
first_indexed	2023-09-18T21:10:32Z
last_indexed	2023-09-18T21:10:32Z
_version_	1777411222091595776

Experimental investigations on wall pressure in suddenly enlarged ducts at supersonic Mach number regimes

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