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A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose

The most challenging task concerning wind tunnel description is, to ascertain the supporting mechanism at high-speed flows inside test section with least complexity and low-cost. This paper presents the design and development of a simple and cost effective test section for a subsonic compressible wi...

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Main Authors: Al-Robaian, Abdul Rehman A, Khan, Sher Afghan, Asad Ullah, Mohammed, G. M., Fharrukh Ahmed, Imtiyaz, A
Format: Article
Language:English
English
Published: Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC PVT. LTD.) 2018
Subjects:
TL500 Aeronautics
Online Access:http://irep.iium.edu.my/67482/1/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic.pdf
http://irep.iium.edu.my/67482/2/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic_SCOPUS.pdf
http://irep.iium.edu.my/67482/
http://www.tjprc.org/publishpapers/2-67-1541585018-43.IJMPERDDEC201843.pdf
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spelling my.iium.irep.674822018-12-31T08:45:02Z http://irep.iium.edu.my/67482/ A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose Al-Robaian, Abdul Rehman A Khan, Sher Afghan Asad Ullah, Mohammed G. M., Fharrukh Ahmed Imtiyaz, A TL500 Aeronautics The most challenging task concerning wind tunnel description is, to ascertain the supporting mechanism at high-speed flows inside test section with least complexity and low-cost. This paper presents the design and development of a simple and cost effective test section for a subsonic compressible wind tunnel for educational purpose. The objective of this open-type wind tunnel was to demonstrate flow around model without any interference at high speeds. In this work, that is study of flow analysis, a subsonic square nozzle was fabricated to achieve maximum velocity of 340 m/s. The test section is 25 mm x 25 mm x 70 mm and is externally attached with travers. It starts from length 25 mm to avoid dead zone and ends at 95 mm to avoid end effects, and on one of the surfaces pressure taps were provided for measuring pressure at different locations inside the wall of duct. The duct length was taken as 100 mm and the pressure taps were at the distance of 8 mm, 16 mm, 24 mm, 49 mm, 59 mm, 80 mm and 90 mm to measure wall pressure. They were connected to sensors through PVC tubes and further to DAQ using LabVIEW interface, and finally to the computer. In addition to this, the flow through the duct can be visualized using transparent glass to find the reattachment point for our re-circulation bubble. A new concept of attaching models in a 3 D traverse was found very easy for inserting it from behind in test section, and thereby interference and breaking of strings was eliminated. Calibration was done through pitot tube at the exit of test section in y and z direction. The nature of graph tells about the correctness of the designed wind tunnel test section. After calibration, we found that the exit velocity is constant for approximately 80 percent area. This area is the effective test section work area. Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC PVT. LTD.) 2018-12 Article PeerReviewed application/pdf en http://irep.iium.edu.my/67482/1/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic.pdf application/pdf en http://irep.iium.edu.my/67482/2/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic_SCOPUS.pdf Al-Robaian, Abdul Rehman A and Khan, Sher Afghan and Asad Ullah, Mohammed and G. M., Fharrukh Ahmed and Imtiyaz, A (2018) A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose. International Journal of Mechanical and Production Engineering Research and Development (IJMPERD), 8 (6). pp. 383-394. ISSN 2249-6890 http://www.tjprc.org/publishpapers/2-67-1541585018-43.IJMPERDDEC201843.pdf 10.24247/ijmperddec201843
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
English
topic TL500 Aeronautics
spellingShingle TL500 Aeronautics
Al-Robaian, Abdul Rehman A
Khan, Sher Afghan
Asad Ullah, Mohammed
G. M., Fharrukh Ahmed
Imtiyaz, A
A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
description The most challenging task concerning wind tunnel description is, to ascertain the supporting mechanism at high-speed flows inside test section with least complexity and low-cost. This paper presents the design and development of a simple and cost effective test section for a subsonic compressible wind tunnel for educational purpose. The objective of this open-type wind tunnel was to demonstrate flow around model without any interference at high speeds. In this work, that is study of flow analysis, a subsonic square nozzle was fabricated to achieve maximum velocity of 340 m/s. The test section is 25 mm x 25 mm x 70 mm and is externally attached with travers. It starts from length 25 mm to avoid dead zone and ends at 95 mm to avoid end effects, and on one of the surfaces pressure taps were provided for measuring pressure at different locations inside the wall of duct. The duct length was taken as 100 mm and the pressure taps were at the distance of 8 mm, 16 mm, 24 mm, 49 mm, 59 mm, 80 mm and 90 mm to measure wall pressure. They were connected to sensors through PVC tubes and further to DAQ using LabVIEW interface, and finally to the computer. In addition to this, the flow through the duct can be visualized using transparent glass to find the reattachment point for our re-circulation bubble. A new concept of attaching models in a 3 D traverse was found very easy for inserting it from behind in test section, and thereby interference and breaking of strings was eliminated. Calibration was done through pitot tube at the exit of test section in y and z direction. The nature of graph tells about the correctness of the designed wind tunnel test section. After calibration, we found that the exit velocity is constant for approximately 80 percent area. This area is the effective test section work area.
format Article
author Al-Robaian, Abdul Rehman A
Khan, Sher Afghan
Asad Ullah, Mohammed
G. M., Fharrukh Ahmed
Imtiyaz, A
author_facet Al-Robaian, Abdul Rehman A
Khan, Sher Afghan
Asad Ullah, Mohammed
G. M., Fharrukh Ahmed
Imtiyaz, A
author_sort Al-Robaian, Abdul Rehman A
title A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
title_short A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
title_full A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
title_fullStr A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
title_full_unstemmed A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
title_sort new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose
publisher Transstellar Journal Publications and Research Consultancy Private Limited (TJPRC PVT. LTD.)
publishDate 2018
url http://irep.iium.edu.my/67482/1/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic.pdf
http://irep.iium.edu.my/67482/2/67482_A%20new%20approach%20to%20low-cost%20open-typed%20subsonic_SCOPUS.pdf
http://irep.iium.edu.my/67482/
http://www.tjprc.org/publishpapers/2-67-1541585018-43.IJMPERDDEC201843.pdf
_version_ 1643618529391411200
score 13.211869

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