Exprimental study suddenly expanded flow from correctly expanded nozzles

This paper presents the results of the experimental investigation conducted at supersonic Mach numbers through converging-diverging nozzles. The experiments were conducted for correctly expanded cases and, for length-to-diameter ratio of 10 to 1. The area ratios were 2.56, 3.24, 4.84, and 6.25. Th...

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Main Authors:	Fharukh, G M, Asad Ullah, M, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	Asian Research Publishing Network (ARPN). 2016
Subjects:	TL1 Motor vehicles
Online Access:	http://irep.iium.edu.my/51911/ http://irep.iium.edu.my/51911/ http://irep.iium.edu.my/51911/1/jeas_0816_4879.pdf http://irep.iium.edu.my/51911/9/51911_Experimental%20study_Scopus.pdf

id	iium-51911
recordtype	eprints
spelling	iium-519112017-04-13T07:50:10Z http://irep.iium.edu.my/51911/ Exprimental study suddenly expanded flow from correctly expanded nozzles Fharukh, G M Asad Ullah, M Khan, Sher Afghan TL1 Motor vehicles This paper presents the results of the experimental investigation conducted at supersonic Mach numbers through converging-diverging nozzles. The experiments were conducted for correctly expanded cases and, for length-to-diameter ratio of 10 to 1. The area ratios were 2.56, 3.24, 4.84, and 6.25. The results presented are only for correctly expanded jets. From the results it is found that at lower Mach numbers and area ratios the efficacy of the control in the form of micro jets is only marginal and the control results in increase of base pressure for all the Mach number. For the first two lower area ratios namely 2.56 and 3.24, it is also observed that the magnitude is getting enhanced considerably from Mach 1.6 and beyond, but for the larger area ratios namely 4.84 and 6.25 of the present study the control results in decrease of base pressure for Mach numbers in the range 1.6, 1.8, and 2.0. When we analyzed and plotted the wall pressure distribution in the enlarged duct the flow remains unperturbed and attached with the suddenly expanded duct for both with and without control cases. For Mach 1.48 the flow field in the duct becomes oscillatory which; indicates that the flow in the duct is dominated by the waves and when the active control is employed suppresses the noise, and this peculiar phenomenon happens only for this Mach number. However, for Mach 1.8 and 2.0 the flow structure in the duct remained oscillatory for the entire region of the duct, and for rest of the Mach numbers it remained same even when the control in the form of micro jets are activated. Hence, it can be stated that the control with the micro jets does influence the flow in the duct wall adversely except at Mach 1.48. Asian Research Publishing Network (ARPN). 2016-08-20 Article PeerReviewed application/pdf en http://irep.iium.edu.my/51911/1/jeas_0816_4879.pdf application/pdf en http://irep.iium.edu.my/51911/9/51911_Experimental%20study_Scopus.pdf Fharukh, G M and Asad Ullah, M and Khan, Sher Afghan (2016) Exprimental study suddenly expanded flow from correctly expanded nozzles. ARPN Journal of Engineering and Applied Sciences, 11 (16). pp. 10041-10047. ISSN 1819-6608 http://www.arpnjournals.org/jeas/research_papers/rp_2016/jeas_0816_4879.pdf
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
spellingShingle	TL1 Motor vehicles Fharukh, G M Asad Ullah, M Khan, Sher Afghan Exprimental study suddenly expanded flow from correctly expanded nozzles
description	This paper presents the results of the experimental investigation conducted at supersonic Mach numbers through converging-diverging nozzles. The experiments were conducted for correctly expanded cases and, for length-to-diameter ratio of 10 to 1. The area ratios were 2.56, 3.24, 4.84, and 6.25. The results presented are only for correctly expanded jets. From the results it is found that at lower Mach numbers and area ratios the efficacy of the control in the form of micro jets is only marginal and the control results in increase of base pressure for all the Mach number. For the first two lower area ratios namely 2.56 and 3.24, it is also observed that the magnitude is getting enhanced considerably from Mach 1.6 and beyond, but for the larger area ratios namely 4.84 and 6.25 of the present study the control results in decrease of base pressure for Mach numbers in the range 1.6, 1.8, and 2.0. When we analyzed and plotted the wall pressure distribution in the enlarged duct the flow remains unperturbed and attached with the suddenly expanded duct for both with and without control cases. For Mach 1.48 the flow field in the duct becomes oscillatory which; indicates that the flow in the duct is dominated by the waves and when the active control is employed suppresses the noise, and this peculiar phenomenon happens only for this Mach number. However, for Mach 1.8 and 2.0 the flow structure in the duct remained oscillatory for the entire region of the duct, and for rest of the Mach numbers it remained same even when the control in the form of micro jets are activated. Hence, it can be stated that the control with the micro jets does influence the flow in the duct wall adversely except at Mach 1.48.
format	Article
author	Fharukh, G M Asad Ullah, M Khan, Sher Afghan
author_facet	Fharukh, G M Asad Ullah, M Khan, Sher Afghan
author_sort	Fharukh, G M
title	Exprimental study suddenly expanded flow from correctly expanded nozzles
title_short	Exprimental study suddenly expanded flow from correctly expanded nozzles
title_full	Exprimental study suddenly expanded flow from correctly expanded nozzles
title_fullStr	Exprimental study suddenly expanded flow from correctly expanded nozzles
title_full_unstemmed	Exprimental study suddenly expanded flow from correctly expanded nozzles
title_sort	exprimental study suddenly expanded flow from correctly expanded nozzles
publisher	Asian Research Publishing Network (ARPN).
publishDate	2016
url	http://irep.iium.edu.my/51911/ http://irep.iium.edu.my/51911/ http://irep.iium.edu.my/51911/1/jeas_0816_4879.pdf http://irep.iium.edu.my/51911/9/51911_Experimental%20study_Scopus.pdf
first_indexed	2023-09-18T21:13:36Z
last_indexed	2023-09-18T21:13:36Z
_version_	1777411415164846080

Exprimental study suddenly expanded flow from correctly expanded nozzles

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