Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56

In this paper, the outcome of the experimental investigation and the flow field development in the duct at a supersonic Mach number of 1.2 is presented. The experiments were conducted at various NPR which covers the condition of correct expansion and under expansion. A Convergent-divergent (C-D) noz...

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Main Authors:	Khan, Sher Afghan, Aabid, Abdul, Chaudhary, Zakir Ilahi
Format:	Article
Language:	English English
Published:	Blue Eyes Intelligence Engineering & Sciences 2019
Subjects:	TL780 Rockets
Online Access:	http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/1/73657_Influence%20of%20Control%20Mechanism.pdf http://irep.iium.edu.my/73657/7/73657_Influence%20of%20control%20mechanism%20on%20the%20flow%20field%20of%20duct%20at%20mach%201.2%20for%20area%20ratio%202.56_Scopus.pdf

id	iium-73657
recordtype	eprints
spelling	iium-736572019-11-24T16:19:55Z http://irep.iium.edu.my/73657/ Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56 Khan, Sher Afghan Aabid, Abdul Chaudhary, Zakir Ilahi TL780 Rockets In this paper, the outcome of the experimental investigation and the flow field development in the duct at a supersonic Mach number of 1.2 is presented. The experiments were conducted at various NPR which covers the condition of correct expansion and under expansion. A Convergent-divergent (C-D) nozzle which is connected with the suddenly expanded duct of the diameter of 16 mm of area ratio 2.56. The recirculation zone is controlled by using the microjets of 1 mm of orifice diameter which is placed at 90 degrees interval at 6.5 mm from the central axis of the main jet. The L/D of the duct was used in the investigation was from 1 to 10, and the NPR at which the experiments were conducted considered are in the range from 3, 5, 7, 9 and 11 Blue Eyes Intelligence Engineering & Sciences 2019-07-25 Article PeerReviewed application/pdf en http://irep.iium.edu.my/73657/1/73657_Influence%20of%20Control%20Mechanism.pdf application/pdf en http://irep.iium.edu.my/73657/7/73657_Influence%20of%20control%20mechanism%20on%20the%20flow%20field%20of%20duct%20at%20mach%201.2%20for%20area%20ratio%202.56_Scopus.pdf Khan, Sher Afghan and Aabid, Abdul and Chaudhary, Zakir Ilahi (2019) Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56. International Journal of Innovative Technology and Exploring Engineering (IJITEE), 8 (6S4). pp. 1135-1138. ISSN 2278-3075 https://www.ijitee.org/wp-content/uploads/papers/v8i6s4/F12360486S419.pdf 10.35940/ijitee.F1236.0486S419
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English English
topic	TL780 Rockets
spellingShingle	TL780 Rockets Khan, Sher Afghan Aabid, Abdul Chaudhary, Zakir Ilahi Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
description	In this paper, the outcome of the experimental investigation and the flow field development in the duct at a supersonic Mach number of 1.2 is presented. The experiments were conducted at various NPR which covers the condition of correct expansion and under expansion. A Convergent-divergent (C-D) nozzle which is connected with the suddenly expanded duct of the diameter of 16 mm of area ratio 2.56. The recirculation zone is controlled by using the microjets of 1 mm of orifice diameter which is placed at 90 degrees interval at 6.5 mm from the central axis of the main jet. The L/D of the duct was used in the investigation was from 1 to 10, and the NPR at which the experiments were conducted considered are in the range from 3, 5, 7, 9 and 11
format	Article
author	Khan, Sher Afghan Aabid, Abdul Chaudhary, Zakir Ilahi
author_facet	Khan, Sher Afghan Aabid, Abdul Chaudhary, Zakir Ilahi
author_sort	Khan, Sher Afghan
title	Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
title_short	Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
title_full	Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
title_fullStr	Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
title_full_unstemmed	Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56
title_sort	influence of control mechanism on the flow field of duct at mach 1.2 for area ratio 2.56
publisher	Blue Eyes Intelligence Engineering & Sciences
publishDate	2019
url	http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/ http://irep.iium.edu.my/73657/1/73657_Influence%20of%20Control%20Mechanism.pdf http://irep.iium.edu.my/73657/7/73657_Influence%20of%20control%20mechanism%20on%20the%20flow%20field%20of%20duct%20at%20mach%201.2%20for%20area%20ratio%202.56_Scopus.pdf
first_indexed	2023-09-18T21:44:25Z
last_indexed	2023-09-18T21:44:25Z
_version_	1777413354204168192

Influence of control mechanism on the flow field of duct at Mach 1.2 for area ratio 2.56

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