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Research Article | Open Access
Volume 2 | Issue 6 | Year 2015 | Article Id. IJME-V2I6P104 | DOI : https://doi.org/10.14445/23488360/IJME-V2I6P104

Study of NACA 4412 and Selig 1223 airfoils through computational fluid dynamics

Jasminder Singh, Dr. Jaswinder Singh, Ampritpal Singh , Abhishek Rana, Ajay Dahiya

Citation :

Jasminder Singh, Dr. Jaswinder Singh, Ampritpal Singh , Abhishek Rana, Ajay Dahiya, "Study of NACA 4412 and Selig 1223 airfoils through computational fluid dynamics," International Journal of Mechanical Engineering, vol. 2, no. 6, pp. 17-21, 2015. Crossref, https://doi.org/10.14445/23488360/IJME-V2I6P104

Abstract

NACA (national advisory committee for aeronautics) airfoils have been generated according to the NACA standards. The effects of fluid flow have been studied over the two airfoils 4412 and S1223 through computational fluid dynamics. The comparison was done on the basis coefficient of lift and coefficient of drag. The angle of attack was varied and their effect was seen on velocity, pressure, coefficient of lift and coefficient of drag. In the present research the angle of attack will be varied from 0 degree to 15 degree with the increment of 5 degree.

Keywords

Angle of Attack, CFD Analysis, NACA 4412, S1223 airfoils

References

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