Design of Mini Wind Tunnel Based on Coanda Effect

Yassen El-Sayed Yassen; Ahmed Sharaf Abdelhamed

doi:doi:10.11648/j.ajae.s.2015020101.13

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Design of Mini Wind Tunnel Based on Coanda Effect

Yassen El-Sayed Yassen, Ahmed Sharaf Abdelhamed

Published in American Journal of Aerospace Engineering (Volume 2, Issue 1-1)

Received: 26 September 2014 Accepted: 27 September 2014 Published: 7 October 2014

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Abstract

An experimental investigation and CFD treatment were employed to design mini-wind tunnel based on Coanda effect for model tests and basic research. The inlet source flow is efficiently creating smooth steady airflow with acceptable noise, achieving the possibility of placing the test target closer to the source of flow with reasonable estimates of turbulence intensity. The design aims at achieving flow uniformity in the working section midplane, preventing separation in the contraction and minimizing the boundary–layer thickness. Intensive measurements after construction demonstrate the significance of the design process and validate the CFD predictions. The results are represented in graphic form to indicate the aspects of the contraction ratio. The numerical and experimental results show the uniformity of velocity distribution inside the working section. Tracing of separation and backflow is crucial allowing a variety of realistic demonstrations to be performed. The numerical solution provides a powerful tool to demonstrate the rate of boundary–layer growth inside the working section and validate against the empirical correlations with insignificant wall–friction drag. Assessment study to address large–scale wind tunnel based on coanda effect would be considered.

Published in	American Journal of Aerospace Engineering (Volume 2, Issue 1-1) This article belongs to the Special Issue Hands-on Learning Technique for Multidisciplinary Engineering Education
DOI	10.11648/j.ajae.s.2015020101.13
Page(s)	31-37
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2024. Published by Science Publishing Group

Keywords

Separation, CFD, Coanda Effect, Mini–Wind–Tunnel, Boundary–Layer Growth

References

[1]	Bradshaw, P., and Pankhurst, R. C., "The design of low-speed wind tunnels", Progress in aeronautical sciences 6, 1 – 69, 1964.
[2]	Mehta, R.D., "Aspects of the Design and Performance of Blower Wind Tunnels Components", Ph.D. Thesis, Department of Aeronautics, Imperial College, University of London, 1978.
[3]	Mehta, R.D. and Bradshaw, P., "Design Rules for Small Low Speed Wind Tunnels", Aeronaut. J., Vol. 83, No. 827, pp. 443-449, 1979.
[4]	Bell, J.H., and Mehta, R.D., " Contraction Design for Small Law-Speed Wind Tunnels", National Aeronautics and space, CA 94305, 1988.
[5]	Rae, W. H., and Pope, A., "Low-speed wind tunnel testing", 2nd edn. John Wiley and sons, 1984.
[6]	Mansi, S., Neha, S., and Sunil, K. Y., "Review of Design and Construction of an Open Circuit Low Speed Wind Tunnel", Global J. of Researches in Eing. (A), V. XIII Issue V Version I, 2013.
[7]	Björn L., and Arne V. J., "Design and Evaluation of a Low-Speed Wind-Tunnel with Expanding Corners", Technical Reports from Royal Institute of Technology, Department of Mechanics, SE-100 44 Stockholm, Sweden, 2002.
[8]	Seidel, M., "Construction, design, manufacturing, and calibration of the German-Dutch wind tunnel (DNW)", Tech. Rep., Duits-Nederlandese Windtunnel (DNW), 1982.
[9]	Goldstein, E.,"Wind Tunnels, Don't Count Them Out," Aerospace America, Vol. 48 4, pp. 38-43, 2010.
[10]	Salam, C.A., and Ali, M.A., "Design and Fabrication of A Bench Mounted Closed Loop Wind Tunnel", MIST J. of Science and technology, Vol. 2, No. 1, 2010.
[11]	Wagner, S., Bareiß, R. and Guidati, G, "Wind Turbine Noise", Springer-Verlag, Berlin, pp. 14-21, 1996.

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APA Style

Yassen El-Sayed Yassen, Ahmed Sharaf Abdelhamed. (2014). Design of Mini Wind Tunnel Based on Coanda Effect. American Journal of Aerospace Engineering, 2(1-1), 31-37. https://doi.org/10.11648/j.ajae.s.2015020101.13

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ACS Style

Yassen El-Sayed Yassen; Ahmed Sharaf Abdelhamed. Design of Mini Wind Tunnel Based on Coanda Effect. Am. J. Aerosp. Eng. 2014, 2(1-1), 31-37. doi: 10.11648/j.ajae.s.2015020101.13

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AMA Style

Yassen El-Sayed Yassen, Ahmed Sharaf Abdelhamed. Design of Mini Wind Tunnel Based on Coanda Effect. Am J Aerosp Eng. 2014;2(1-1):31-37. doi: 10.11648/j.ajae.s.2015020101.13

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@article{10.11648/j.ajae.s.2015020101.13,
  author = {Yassen El-Sayed Yassen and Ahmed Sharaf Abdelhamed},
  title = {Design of Mini Wind Tunnel Based on Coanda Effect},
  journal = {American Journal of Aerospace Engineering},
  volume = {2},
  number = {1-1},
  pages = {31-37},
  doi = {10.11648/j.ajae.s.2015020101.13},
  url = {https://doi.org/10.11648/j.ajae.s.2015020101.13},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.s.2015020101.13},
  abstract = {An experimental investigation and CFD treatment were employed to design mini-wind tunnel based on Coanda effect for model tests and basic research. The inlet source flow is efficiently creating smooth steady airflow with acceptable noise, achieving the possibility of placing the test target closer to the source of flow with reasonable estimates of turbulence intensity. The design aims at achieving flow uniformity in the working section midplane, preventing separation in the contraction and minimizing the boundary–layer thickness. Intensive measurements after construction demonstrate the significance of the design process and validate the CFD predictions. The results are represented in graphic form to indicate the aspects of the contraction ratio. The numerical and experimental results show the uniformity of velocity distribution inside the working section. Tracing of separation and backflow is crucial allowing a variety of realistic demonstrations to be performed. The numerical solution provides a powerful tool to demonstrate the rate of boundary–layer growth inside the working section and validate against the empirical correlations with insignificant wall–friction drag. Assessment study to address large–scale wind tunnel based on coanda effect would be considered.},
 year = {2014}
}

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TY  - JOUR
T1  - Design of Mini Wind Tunnel Based on Coanda Effect
AU  - Yassen El-Sayed Yassen
AU  - Ahmed Sharaf Abdelhamed
Y1  - 2014/10/07
PY  - 2014
N1  - https://doi.org/10.11648/j.ajae.s.2015020101.13
DO  - 10.11648/j.ajae.s.2015020101.13
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 31
EP  - 37
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.s.2015020101.13
AB  - An experimental investigation and CFD treatment were employed to design mini-wind tunnel based on Coanda effect for model tests and basic research. The inlet source flow is efficiently creating smooth steady airflow with acceptable noise, achieving the possibility of placing the test target closer to the source of flow with reasonable estimates of turbulence intensity. The design aims at achieving flow uniformity in the working section midplane, preventing separation in the contraction and minimizing the boundary–layer thickness. Intensive measurements after construction demonstrate the significance of the design process and validate the CFD predictions. The results are represented in graphic form to indicate the aspects of the contraction ratio. The numerical and experimental results show the uniformity of velocity distribution inside the working section. Tracing of separation and backflow is crucial allowing a variety of realistic demonstrations to be performed. The numerical solution provides a powerful tool to demonstrate the rate of boundary–layer growth inside the working section and validate against the empirical correlations with insignificant wall–friction drag. Assessment study to address large–scale wind tunnel based on coanda effect would be considered.
VL  - 2
IS  - 1-1
ER  -

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Author Information

Yassen El-Sayed Yassen

Mechanical Power Engineering , Faculty of Engineering, Port Said University, Port Said, Egypt
Ahmed Sharaf Abdelhamed

Mechanical Power Engineering , Faculty of Engineering, Port Said University, Port Said, Egypt

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APA Style

Yassen El-Sayed Yassen, Ahmed Sharaf Abdelhamed. (2014). Design of Mini Wind Tunnel Based on Coanda Effect. American Journal of Aerospace Engineering, 2(1-1), 31-37. https://doi.org/10.11648/j.ajae.s.2015020101.13

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ACS Style

Yassen El-Sayed Yassen; Ahmed Sharaf Abdelhamed. Design of Mini Wind Tunnel Based on Coanda Effect. Am. J. Aerosp. Eng. 2014, 2(1-1), 31-37. doi: 10.11648/j.ajae.s.2015020101.13

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AMA Style

Yassen El-Sayed Yassen, Ahmed Sharaf Abdelhamed. Design of Mini Wind Tunnel Based on Coanda Effect. Am J Aerosp Eng. 2014;2(1-1):31-37. doi: 10.11648/j.ajae.s.2015020101.13

Copy | Download

@article{10.11648/j.ajae.s.2015020101.13,
  author = {Yassen El-Sayed Yassen and Ahmed Sharaf Abdelhamed},
  title = {Design of Mini Wind Tunnel Based on Coanda Effect},
  journal = {American Journal of Aerospace Engineering},
  volume = {2},
  number = {1-1},
  pages = {31-37},
  doi = {10.11648/j.ajae.s.2015020101.13},
  url = {https://doi.org/10.11648/j.ajae.s.2015020101.13},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajae.s.2015020101.13},
  abstract = {An experimental investigation and CFD treatment were employed to design mini-wind tunnel based on Coanda effect for model tests and basic research. The inlet source flow is efficiently creating smooth steady airflow with acceptable noise, achieving the possibility of placing the test target closer to the source of flow with reasonable estimates of turbulence intensity. The design aims at achieving flow uniformity in the working section midplane, preventing separation in the contraction and minimizing the boundary–layer thickness. Intensive measurements after construction demonstrate the significance of the design process and validate the CFD predictions. The results are represented in graphic form to indicate the aspects of the contraction ratio. The numerical and experimental results show the uniformity of velocity distribution inside the working section. Tracing of separation and backflow is crucial allowing a variety of realistic demonstrations to be performed. The numerical solution provides a powerful tool to demonstrate the rate of boundary–layer growth inside the working section and validate against the empirical correlations with insignificant wall–friction drag. Assessment study to address large–scale wind tunnel based on coanda effect would be considered.},
 year = {2014}
}

Copy | Download

TY  - JOUR
T1  - Design of Mini Wind Tunnel Based on Coanda Effect
AU  - Yassen El-Sayed Yassen
AU  - Ahmed Sharaf Abdelhamed
Y1  - 2014/10/07
PY  - 2014
N1  - https://doi.org/10.11648/j.ajae.s.2015020101.13
DO  - 10.11648/j.ajae.s.2015020101.13
T2  - American Journal of Aerospace Engineering
JF  - American Journal of Aerospace Engineering
JO  - American Journal of Aerospace Engineering
SP  - 31
EP  - 37
PB  - Science Publishing Group
SN  - 2376-4821
UR  - https://doi.org/10.11648/j.ajae.s.2015020101.13
AB  - An experimental investigation and CFD treatment were employed to design mini-wind tunnel based on Coanda effect for model tests and basic research. The inlet source flow is efficiently creating smooth steady airflow with acceptable noise, achieving the possibility of placing the test target closer to the source of flow with reasonable estimates of turbulence intensity. The design aims at achieving flow uniformity in the working section midplane, preventing separation in the contraction and minimizing the boundary–layer thickness. Intensive measurements after construction demonstrate the significance of the design process and validate the CFD predictions. The results are represented in graphic form to indicate the aspects of the contraction ratio. The numerical and experimental results show the uniformity of velocity distribution inside the working section. Tracing of separation and backflow is crucial allowing a variety of realistic demonstrations to be performed. The numerical solution provides a powerful tool to demonstrate the rate of boundary–layer growth inside the working section and validate against the empirical correlations with insignificant wall–friction drag. Assessment study to address large–scale wind tunnel based on coanda effect would be considered.
VL  - 2
IS  - 1-1
ER  -

Copy | Download