Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56

Airflow from convergent-divergent axisymmetric nozzles expanded into circular duct of higher area were studied experimentally, with the main focus on the flow development in the duct. The flow parameters considered in this investigation are the Mach number at the nozzle exit and the level of expansi...

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Main Authors:	Bashir, Musavir, Baig, Maughal Ahmed Al, Ismail, Ahmad Faris, Khan, Sher Afghan
Format:	Article
Language:	English
Published:	IOSR journals 2016
Subjects:	TL Motor vehicles. Aeronautics. Astronautics TL1 Motor vehicles
Online Access:	http://irep.iium.edu.my/54294/ http://irep.iium.edu.my/54294/ http://irep.iium.edu.my/54294/1/Musavir.pdf

id	iium-54294
recordtype	eprints
spelling	iium-542942017-01-23T07:35:19Z http://irep.iium.edu.my/54294/ Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56 Bashir, Musavir Baig, Maughal Ahmed Al Ismail, Ahmad Faris Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics TL1 Motor vehicles Airflow from convergent-divergent axisymmetric nozzles expanded into circular duct of higher area were studied experimentally, with the main focus on the flow development in the duct. The flow parameters considered in this investigation are the Mach number at the nozzle exit and the level of expansion. The geometrical parameters considered are the area ratio and the L/D ratio of the duct. To control on the flow field developed in the duct, four tiny jets of 0.5 mm radius located at 90 degrees intervals at 6.5 mm radius from the centre of the nozzle exit were employed as the flow regulators. The Mach number in this case was 1.48. The area ratio of the study was 2.56. The nozzle pressure ratio (NPR) used was from 3.27 and 5.35 respectively which corresponds to ideally expanded and under expanded cases. The L/D ratio of the enlarged duct was varied from 10 to 1. From the results it is found that there is a jump in the wall pressure when flow passes through first oblique shock and this trend is repeated for all the cases.From the results it is found that the entire flow field is full of waves and flow remains identical with and without control when the jets were operated under favourable and adverse pressure gradient, it is also observed that when flow regulators in the form of tiny jets are employed they do not disturb the flow of duct. IOSR journals 2016-12 Article PeerReviewed application/pdf en http://irep.iium.edu.my/54294/1/Musavir.pdf Bashir, Musavir and Baig, Maughal Ahmed Al and Ismail, Ahmad Faris and Khan, Sher Afghan (2016) Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56. IOSR journal of Mechanical & Civil Engineering, 3. pp. 76-82. ISSN 2320-334x E-ISSN 2278-1684 http://www.iosrjournals.org/
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 TL1 Motor vehicles
spellingShingle	TL Motor vehicles. Aeronautics. Astronautics TL1 Motor vehicles Bashir, Musavir Baig, Maughal Ahmed Al Ismail, Ahmad Faris Khan, Sher Afghan Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
description	Airflow from convergent-divergent axisymmetric nozzles expanded into circular duct of higher area were studied experimentally, with the main focus on the flow development in the duct. The flow parameters considered in this investigation are the Mach number at the nozzle exit and the level of expansion. The geometrical parameters considered are the area ratio and the L/D ratio of the duct. To control on the flow field developed in the duct, four tiny jets of 0.5 mm radius located at 90 degrees intervals at 6.5 mm radius from the centre of the nozzle exit were employed as the flow regulators. The Mach number in this case was 1.48. The area ratio of the study was 2.56. The nozzle pressure ratio (NPR) used was from 3.27 and 5.35 respectively which corresponds to ideally expanded and under expanded cases. The L/D ratio of the enlarged duct was varied from 10 to 1. From the results it is found that there is a jump in the wall pressure when flow passes through first oblique shock and this trend is repeated for all the cases.From the results it is found that the entire flow field is full of waves and flow remains identical with and without control when the jets were operated under favourable and adverse pressure gradient, it is also observed that when flow regulators in the form of tiny jets are employed they do not disturb the flow of duct.
format	Article
author	Bashir, Musavir Baig, Maughal Ahmed Al Ismail, Ahmad Faris Khan, Sher Afghan
author_facet	Bashir, Musavir Baig, Maughal Ahmed Al Ismail, Ahmad Faris Khan, Sher Afghan
author_sort	Bashir, Musavir
title	Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
title_short	Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
title_full	Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
title_fullStr	Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
title_full_unstemmed	Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
title_sort	control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56
publisher	IOSR journals
publishDate	2016
url	http://irep.iium.edu.my/54294/ http://irep.iium.edu.my/54294/ http://irep.iium.edu.my/54294/1/Musavir.pdf
first_indexed	2023-09-18T21:16:50Z
last_indexed	2023-09-18T21:16:50Z
_version_	1777411618535112704

Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56

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