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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International Organization of Scientific Research ( IOSR )
2016
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| Online Access: | http://irep.iium.edu.my/54286/ http://irep.iium.edu.my/54286/ http://irep.iium.edu.my/54286/ http://irep.iium.edu.my/54286/1/Asadullah.pdf |
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iium-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 PeerReviewed 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 E-ISSN 2278-1684 http://www.iosrjournals.org/iosr-jmce/papers/i-%20CAM2K16-2016/Mech/Volume%203/15.%2090-98.pdf 10.9790/1684-16053039098 |
| repository_type |
Digital Repository |
| institution_category |
Local University |
| institution |
International Islamic University Malaysia |
| building |
IIUM Repository |
| collection |
Online Access |
| 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/ http://irep.iium.edu.my/54286/ http://irep.iium.edu.my/54286/ http://irep.iium.edu.my/54286/1/Asadullah.pdf |
| first_indexed |
2023-09-18T21:16:49Z |
| last_indexed |
2023-09-18T21:16:49Z |
| _version_ |
1777411617387970560 |