Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number

B. S. Anil Kumar; Ramalingaiah; S. Manjunath; Rudresh Ganganna

doi:doi:10.11648/j.ijsts.20150306.17

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Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number

B. S. Anil Kumar, Ramalingaiah, S. Manjunath, Rudresh Ganganna

Published in International Journal of Science, Technology and Society (Volume 3, Issue 6)

Received: 2 November 2015 Accepted: 25 November 2015 Published: 4 January 2016

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Abstract

The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using Spalart Allmaras turbulence model, K-omega SST turbulence model with flow transition capabilities, Standard K-Epsilon Turbulence model and K-omega SST turbulence model.It is to be noted that each turbulence model employs different mathematical approach to model boundary layer. The analysis results are then compared with the wind tunnel results and the performance of the turbulence models are discussed. This study recommends an accurate methodology to conduct CFD analysis for external aerodynamic flows.

Published in	International Journal of Science, Technology and Society (Volume 3, Issue 6)
DOI	10.11648/j.ijsts.20150306.17
Page(s)	315-321
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), 2016. Published by Science Publishing Group

Keywords

NACA 23024, Turbulence Models, Lift Curve, Drag Curve, Stalling

References

[1]	David Hartwanger et.al “3 D modeling of a Wind Turbine using CFD” NAFEMS Conference, United Kingdom, 2008.
[2]	Frank Bertagnolio et.al “Wind Turbine airfoil catalogue” RISOE National Laboratories, Denmark, 2001.
[3]	H. Gao et.al “Computational study of unsteady flows around dragonfly and smooth airfoils at low Reynolds number” 46^th AIAA Aerospace sciences meeting and exhibit, Reno, Navada, 2008.
[4]	Vance Dippold, III, “Investigation of Wall Function and Turbulence Model Performance within the Wind Code”, 43rd AIAA Aerospace Sciences Meeting and Exhibit, 10 - 13 January 2005, Reno, Nevada.
[5]	S. Sarada, M. Shiva Shankar and Rudresh Ganganna “Numerical simulation of Viscous, incompressible flow around NACA 64618 subsonic airfoil using Computational Fluid Dynamics”, Proceedings of National conference on advances in Mechanical Engineering, Allied Publishers Pvt Ltd, 2012.
[6]	Menter, F. R., “Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications” AIAA Journal, Vol. 32, No. 8, August 1994, pp. 1598-1605 (http://turbmodels.larc.nasa.gov/sst.html).
[7]	Abbott. I.H, “Theory of wing section, including a summary of airfoil data”, Dover book on Physics, 1995.
[8]	Menter FR, 1994, Two Equation Eddy-viscosity turbulence model for Engineering Applications, AIAA journal, USA, Volume 32, No.8, pp. 1598-1605.
[9]	Drishtysingh Ramdenee, H. Ibrahim, N. Barka, A. Ilinca, 2013, Modeling of aerodynamic flutter on a naca 4412 airfoil wind blade, International Journal of Simulation and Process Modelling, Inderscience Publishers, Canada, Volume 8, No. 1 , pp. 79-87.
[10]	Douvi C. Eleni, Tsavalos I. Athanasios and Margaris P. Dionissios, Evaluation of the turbulence models for the simulation of the flow over a National Advisory Committee for Aeronautics (NACA) 0012 airfoil, Department of Mechanical Laboratory, University of Patras, 26500 Patras, Greece, Journal of Mechanical Engineering Research Vol 4(3), pp. 100-111, March 2012 ISSN 2141-2383.
[11]	Bacha WA, Ghaly WS (2006). Drag Prediction in Transitional Flow over Two-Dimensional Airfoils, Proceedings of the 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV.
[12]	Menter FR (1994). Two-Equation Eddy-Viscosity Turbulence Models for Engineering Applications. AIAA J., 32: 1598-1605.
[13]	Spalart, PR, Allmaras SR (1992). A One-Equation Turbulence Model for Aerodynamic Flows. AIAA Paper, pp. 92-439.
[14]	Michealamitay, Douglas R Smith, Valdis Kibens, David E. Parekh and Ali Glezer. “Aerodynamic flow control over unconventional airfoil using synthetic jet actuators”. AIAA journal. V39, no1, march 2001.
[15]	Gaurav Saxena, Mahendra Agarwal. “Aerodynamic analysis of NACA 4412 airfoil using CFD”. International journal of emerging trends in engineering and development. Issue 3, vol 4, july 2013.

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APA Style

B. S. Anil Kumar, Ramalingaiah, S. Manjunath, Rudresh Ganganna. (2016). Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. International Journal of Science, Technology and Society, 3(6), 315-321. https://doi.org/10.11648/j.ijsts.20150306.17

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ACS Style

B. S. Anil Kumar; Ramalingaiah; S. Manjunath; Rudresh Ganganna. Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. Int. J. Sci. Technol. Soc. 2016, 3(6), 315-321. doi: 10.11648/j.ijsts.20150306.17

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AMA Style

B. S. Anil Kumar, Ramalingaiah, S. Manjunath, Rudresh Ganganna. Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. Int J Sci Technol Soc. 2016;3(6):315-321. doi: 10.11648/j.ijsts.20150306.17

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@article{10.11648/j.ijsts.20150306.17,
  author = {B. S. Anil Kumar and Ramalingaiah and S. Manjunath and Rudresh Ganganna},
  title = {Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number},
  journal = {International Journal of Science, Technology and Society},
  volume = {3},
  number = {6},
  pages = {315-321},
  doi = {10.11648/j.ijsts.20150306.17},
  url = {https://doi.org/10.11648/j.ijsts.20150306.17},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijsts.20150306.17},
  abstract = {The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using Spalart Allmaras turbulence model, K-omega SST turbulence model with flow transition capabilities, Standard K-Epsilon Turbulence model and K-omega SST turbulence model.It is to be noted that each turbulence model employs different mathematical approach to model boundary layer. The analysis results are then compared with the wind tunnel results and the performance of the turbulence models are discussed. This study recommends an accurate methodology to conduct CFD analysis for external aerodynamic flows.},
 year = {2016}
}

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TY  - JOUR
T1  - Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number
AU  - B. S. Anil Kumar
AU  - Ramalingaiah
AU  - S. Manjunath
AU  - Rudresh Ganganna
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DO  - 10.11648/j.ijsts.20150306.17
T2  - International Journal of Science, Technology and Society
JF  - International Journal of Science, Technology and Society
JO  - International Journal of Science, Technology and Society
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PB  - Science Publishing Group
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UR  - https://doi.org/10.11648/j.ijsts.20150306.17
AB  - The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using Spalart Allmaras turbulence model, K-omega SST turbulence model with flow transition capabilities, Standard K-Epsilon Turbulence model and K-omega SST turbulence model.It is to be noted that each turbulence model employs different mathematical approach to model boundary layer. The analysis results are then compared with the wind tunnel results and the performance of the turbulence models are discussed. This study recommends an accurate methodology to conduct CFD analysis for external aerodynamic flows.
VL  - 3
IS  - 6
ER  -

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Author Information

B. S. Anil Kumar

Department of Mechanical Engineering, BNMIT, Visveswaraya Technological University, Bangalore, India
Ramalingaiah

Department of Mechanical Engineering, PESCE, Visveswaraya Technological University, Mandya, India
S. Manjunath

Department of Mathematics, BNMIT, Visveswaraya Technological University, Bangalore, India
Rudresh Ganganna

Niharika Institute of Computational Engineering (NICECFD), Bangalore, India

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APA Style

B. S. Anil Kumar, Ramalingaiah, S. Manjunath, Rudresh Ganganna. (2016). Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. International Journal of Science, Technology and Society, 3(6), 315-321. https://doi.org/10.11648/j.ijsts.20150306.17

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ACS Style

B. S. Anil Kumar; Ramalingaiah; S. Manjunath; Rudresh Ganganna. Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. Int. J. Sci. Technol. Soc. 2016, 3(6), 315-321. doi: 10.11648/j.ijsts.20150306.17

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AMA Style

B. S. Anil Kumar, Ramalingaiah, S. Manjunath, Rudresh Ganganna. Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number. Int J Sci Technol Soc. 2016;3(6):315-321. doi: 10.11648/j.ijsts.20150306.17

Copy | Download

@article{10.11648/j.ijsts.20150306.17,
  author = {B. S. Anil Kumar and Ramalingaiah and S. Manjunath and Rudresh Ganganna},
  title = {Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number},
  journal = {International Journal of Science, Technology and Society},
  volume = {3},
  number = {6},
  pages = {315-321},
  doi = {10.11648/j.ijsts.20150306.17},
  url = {https://doi.org/10.11648/j.ijsts.20150306.17},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijsts.20150306.17},
  abstract = {The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using Spalart Allmaras turbulence model, K-omega SST turbulence model with flow transition capabilities, Standard K-Epsilon Turbulence model and K-omega SST turbulence model.It is to be noted that each turbulence model employs different mathematical approach to model boundary layer. The analysis results are then compared with the wind tunnel results and the performance of the turbulence models are discussed. This study recommends an accurate methodology to conduct CFD analysis for external aerodynamic flows.},
 year = {2016}
}

Copy | Download

TY  - JOUR
T1  - Computational Investigation of Flow Separation over Naca 23024 Airfoil at 6 Million Free Stream Reynolds Number
AU  - B. S. Anil Kumar
AU  - Ramalingaiah
AU  - S. Manjunath
AU  - Rudresh Ganganna
Y1  - 2016/01/04
PY  - 2016
N1  - https://doi.org/10.11648/j.ijsts.20150306.17
DO  - 10.11648/j.ijsts.20150306.17
T2  - International Journal of Science, Technology and Society
JF  - International Journal of Science, Technology and Society
JO  - International Journal of Science, Technology and Society
SP  - 315
EP  - 321
PB  - Science Publishing Group
SN  - 2330-7420
UR  - https://doi.org/10.11648/j.ijsts.20150306.17
AB  - The following work is the CFD analysis of NACA 23024 airfoil. The analysis is carried out for a free stream Reynolds number of 6 million for which the wind tunnel results are available. The CFD analysis is carried out using Ansys Fluent Solver. The analysis is carried out using Spalart Allmaras turbulence model, K-omega SST turbulence model with flow transition capabilities, Standard K-Epsilon Turbulence model and K-omega SST turbulence model.It is to be noted that each turbulence model employs different mathematical approach to model boundary layer. The analysis results are then compared with the wind tunnel results and the performance of the turbulence models are discussed. This study recommends an accurate methodology to conduct CFD analysis for external aerodynamic flows.
VL  - 3
IS  - 6
ER  -

Copy | Download