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Active control of wall pressure flow field at low supersonic Mach numbers

This paper presents an experimental study of airflow from convergent-divergent nozzles discharged into enlarged duct, focusing attention on the flow development in the duct. To investigate the influence of active control on the flow field developed in the duct, the micro jets of 0.05 mm radius orifi...

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Main Authors: Asad Ullah, Mohammed, Bashir, Musavir, Janvekar, Ayub, Khan, Sher Afghan
Format: Article
Language:English
Published: International Organization of Scientific Research ( IOSR ) 2016
Subjects:
TL780 Rockets
Online Access:http://irep.iium.edu.my/54286/1/Asadullah.pdf
http://irep.iium.edu.my/54286/
http://www.iosrjournals.org/iosr-jmce/papers/i-%20CAM2K16-2016/Mech/Volume%203/15.%2090-98.pdf
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spelling my.iium.irep.542862017-01-24T08:58:19Z http://irep.iium.edu.my/54286/ Active control of wall pressure flow field at low supersonic Mach numbers Asad Ullah, Mohammed Bashir, Musavir Janvekar, Ayub Khan, Sher Afghan TL780 Rockets This paper presents an experimental study of airflow from convergent-divergent nozzles discharged into enlarged duct, focusing attention on the flow development in the duct. To investigate the influence of active control on the flow field developed in the duct, the micro jets of 0.05 mm radius orifice placed at 900 interval along the base at 6.5 mm from the main jet were employed. The Mach number of this study was 1.3. The area ratio of the present study was 2.56. The NPR presented are from 3, 5, 7, 9, and 11 respectively. The L/D ratio of the duct was varied from 10 to 1. The level of expansion at the nozzle exit influences the wall pressure very strongly since in the present case all the NPRs of the tests are under expanded. For all the L/D the entire flow field in the duct is full of waves, the few shock wave is so powerful that the wall pressure is equal to the atmospheric pressure or more. At L/D = 3, it is seen that due to the influence of the back pressure the number of compression and expansion waves have reduced drastically. The flow field with and without control is identical. International Organization of Scientific Research ( IOSR ) 2016-12 Article REM application/pdf en http://irep.iium.edu.my/54286/1/Asadullah.pdf Asad Ullah, Mohammed and Bashir, Musavir and Janvekar, Ayub and Khan, Sher Afghan (2016) Active control of wall pressure flow field at low supersonic Mach numbers. IOSR Journal of Mechanical and Civil Engineering (IOSR-JMCE), 3. pp. 90-98. ISSN 2320-334x http://www.iosrjournals.org/iosr-jmce/papers/i-%20CAM2K16-2016/Mech/Volume%203/15.%2090-98.pdf 10.9790/1684-16053039098
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
language English
topic TL780 Rockets
spellingShingle TL780 Rockets
Asad Ullah, Mohammed
Bashir, Musavir
Janvekar, Ayub
Khan, Sher Afghan
Active control of wall pressure flow field at low supersonic Mach numbers
description This paper presents an experimental study of airflow from convergent-divergent nozzles discharged into enlarged duct, focusing attention on the flow development in the duct. To investigate the influence of active control on the flow field developed in the duct, the micro jets of 0.05 mm radius orifice placed at 900 interval along the base at 6.5 mm from the main jet were employed. The Mach number of this study was 1.3. The area ratio of the present study was 2.56. The NPR presented are from 3, 5, 7, 9, and 11 respectively. The L/D ratio of the duct was varied from 10 to 1. The level of expansion at the nozzle exit influences the wall pressure very strongly since in the present case all the NPRs of the tests are under expanded. For all the L/D the entire flow field in the duct is full of waves, the few shock wave is so powerful that the wall pressure is equal to the atmospheric pressure or more. At L/D = 3, it is seen that due to the influence of the back pressure the number of compression and expansion waves have reduced drastically. The flow field with and without control is identical.
format Article
author Asad Ullah, Mohammed
Bashir, Musavir
Janvekar, Ayub
Khan, Sher Afghan
author_facet Asad Ullah, Mohammed
Bashir, Musavir
Janvekar, Ayub
Khan, Sher Afghan
author_sort Asad Ullah, Mohammed
title Active control of wall pressure flow field at low supersonic Mach numbers
title_short Active control of wall pressure flow field at low supersonic Mach numbers
title_full Active control of wall pressure flow field at low supersonic Mach numbers
title_fullStr Active control of wall pressure flow field at low supersonic Mach numbers
title_full_unstemmed Active control of wall pressure flow field at low supersonic Mach numbers
title_sort active control of wall pressure flow field at low supersonic mach numbers
publisher International Organization of Scientific Research ( IOSR )
publishDate 2016
url http://irep.iium.edu.my/54286/1/Asadullah.pdf
http://irep.iium.edu.my/54286/
http://www.iosrjournals.org/iosr-jmce/papers/i-%20CAM2K16-2016/Mech/Volume%203/15.%2090-98.pdf
_version_ 1643614521885982720
score 13.211869

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