Experiment on of nozzle flow with sudden expansion at Mach 1.1

This present study discusses the outcome of the experimental investigations, and the efficacy of the tiny jets used to regulate the base pressure as well as the wall pressure in suddenly expanded flow. The control mechanism as tiny jets having a cross-section of 1 mm diameter was employed as the bas...

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Main Authors:	Faheem, Mohammad, Kareem Ullah, Mohammad, Aabid, Abdul, Mokashi, Imran, Khan, Sher Afghan
Format:	Article
Language:	English English
Published:	Blue Eyes Intelligence Engineering & Sciences Publication 2019
Subjects:	TL Motor vehicles. Aeronautics. Astronautics
Online Access:	http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/7/74937%20Experiment%20on%20of%20Nozzle%20Flow.pdf http://irep.iium.edu.my/74937/13/74937_Experiment%20on%20of%20nozzle%20flow%20with%20sudden%20expansion%20at%20mach%201.1_Scopus.pdf

id	iium-74937
recordtype	eprints
spelling	iium-749372019-11-24T16:00:10Z http://irep.iium.edu.my/74937/ Experiment on of nozzle flow with sudden expansion at Mach 1.1 Faheem, Mohammad Kareem Ullah, Mohammad Aabid, Abdul Mokashi, Imran Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics This present study discusses the outcome of the experimental investigations, and the efficacy of the tiny jets used to regulate the base pressure as well as the wall pressure in suddenly expanded flow. The control mechanism as tiny jets having a cross-section of 1 mm diameter was employed as the base pressure regulator at the exit periphery of the nozzle. The experiments were carried out to investigate and record the flow field at the rear end of the separated flow region for area ratio 4.84. Four tiny jets were placed at a distance of 6.5 mm away from the primary jet coming from the nozzle exit at ninety degrees apart, and the tiny control jets were flowing at sonic Mach number. The actual Mach number of the main jet was 1.1. The experimentation was accomplished at a different level of expansion (i. e., NPR = 3, 5, 7, 9, and 11) and the L/D ratio considered was from 10 to 1. This study mainly focuses on the development of the flow in the suddenly expanded duct, nature of the flow in the duct, and the impact of the Control on the wall pressure and the magnitude of the pressure along the duct. The wall pressure in the smooth duct is not unfavorably influenced by the control jets. Blue Eyes Intelligence Engineering & Sciences Publication 2019-08 Article PeerReviewed application/pdf en http://irep.iium.edu.my/74937/7/74937%20Experiment%20on%20of%20Nozzle%20Flow.pdf application/pdf en http://irep.iium.edu.my/74937/13/74937_Experiment%20on%20of%20nozzle%20flow%20with%20sudden%20expansion%20at%20mach%201.1_Scopus.pdf Faheem, Mohammad and Kareem Ullah, Mohammad and Aabid, Abdul and Mokashi, Imran and Khan, Sher Afghan (2019) Experiment on of nozzle flow with sudden expansion at Mach 1.1. International Journal of Recent Technology and Engineering (IJRTE), 8 (2S8). pp. 1769-1775. E-ISSN 2277-3878 http://www.ijrte.org 10.35940/ijrte.B1150.0882S819
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL Motor vehicles. Aeronautics. Astronautics
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics Faheem, Mohammad Kareem Ullah, Mohammad Aabid, Abdul Mokashi, Imran Khan, Sher Afghan Experiment on of nozzle flow with sudden expansion at Mach 1.1
description	This present study discusses the outcome of the experimental investigations, and the efficacy of the tiny jets used to regulate the base pressure as well as the wall pressure in suddenly expanded flow. The control mechanism as tiny jets having a cross-section of 1 mm diameter was employed as the base pressure regulator at the exit periphery of the nozzle. The experiments were carried out to investigate and record the flow field at the rear end of the separated flow region for area ratio 4.84. Four tiny jets were placed at a distance of 6.5 mm away from the primary jet coming from the nozzle exit at ninety degrees apart, and the tiny control jets were flowing at sonic Mach number. The actual Mach number of the main jet was 1.1. The experimentation was accomplished at a different level of expansion (i. e., NPR = 3, 5, 7, 9, and 11) and the L/D ratio considered was from 10 to 1. This study mainly focuses on the development of the flow in the suddenly expanded duct, nature of the flow in the duct, and the impact of the Control on the wall pressure and the magnitude of the pressure along the duct. The wall pressure in the smooth duct is not unfavorably influenced by the control jets.
format	Article
author	Faheem, Mohammad Kareem Ullah, Mohammad Aabid, Abdul Mokashi, Imran Khan, Sher Afghan
author_facet	Faheem, Mohammad Kareem Ullah, Mohammad Aabid, Abdul Mokashi, Imran Khan, Sher Afghan
author_sort	Faheem, Mohammad
title	Experiment on of nozzle flow with sudden expansion at Mach 1.1
title_short	Experiment on of nozzle flow with sudden expansion at Mach 1.1
title_full	Experiment on of nozzle flow with sudden expansion at Mach 1.1
title_fullStr	Experiment on of nozzle flow with sudden expansion at Mach 1.1
title_full_unstemmed	Experiment on of nozzle flow with sudden expansion at Mach 1.1
title_sort	experiment on of nozzle flow with sudden expansion at mach 1.1
publisher	Blue Eyes Intelligence Engineering & Sciences Publication
publishDate	2019
url	http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/ http://irep.iium.edu.my/74937/7/74937%20Experiment%20on%20of%20Nozzle%20Flow.pdf http://irep.iium.edu.my/74937/13/74937_Experiment%20on%20of%20nozzle%20flow%20with%20sudden%20expansion%20at%20mach%201.1_Scopus.pdf
first_indexed	2023-09-18T21:46:03Z
last_indexed	2023-09-18T21:46:03Z
_version_	1777413456785309696

Experiment on of nozzle flow with sudden expansion at Mach 1.1

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