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Volume 4 | Issue 8 | Year 2013 | Article Id. IJETT-V4I8P103 | DOI : https://doi.org/10.14445/22315381/IJETT-V4I8P103
CFD ANALYSIS OF STATIC PRESSURE AND DYNAMIC PRESSURE FOR NACA 4412
Mr. Arvind Prabhakar
Citation :
Mr. Arvind Prabhakar, "CFD ANALYSIS OF STATIC PRESSURE AND DYNAMIC PRESSURE FOR NACA 4412," International Journal of Engineering Trends and Technology (IJETT), vol. 4, no. 8, pp. 3258-3265, 2013. Crossref, https://doi.org/10.14445/22315381/IJETT-V4I8P103
Abstract
The static pressure and dynamic pressure are important parameters and have a strong influence on airplane wing lift and stagnation point . In this paper NACA 4412 airfoil profile is considered for analysis of an airplane wing .The NACA 4412 airfoil is created using CATIA V5 And CFD analysis is carried out using commercial code ANSYS 13.0 FLUENT at an inlet boundary condition of V sound (i.e. 340.29 m/s) for angles of attack of 0 ?, 6, 12 AND 16 ?. Standard k - ? turbulence model with standard wall function is used for analysis. Variations of static pressure and dynamic pressure are plotted in form of contour.
Keywords
computational fluid dynamics, angle of attack (AOA) , airfoil , Vsound
References
i. http://en.wikipedia.org/wiki/Static_pressure
ii. http://en.wikipedia.org/wiki/Dynamic_pressure
iii. http://kgraham.eng.ua.edu/classes/AEM314/lecture_notes /airfoil_nomenclature.pdf
iv. http://www.ijettjournal.org/volume - 4/issue - 5/IJETT - V4I5P142.pdf
v. ‘Flight Theory and Aerodynamics: A Practical Guide for Operational Safety’ By Charles E. Dole, James E. Lewis
vi. http://flightmechanics.blogspot.in/2010/10/stagnation - point.html
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