AERODYNAMIC CHARACTERISTICS OF AIRFOIL USING PANEL METHOD

Abstract

Potential flow over an airfoil plays an important historical role in the theory of flight. The governing equation for potential flow is Laplace’s equation, a widely studied linear partial differential equation. One of Green’s identities can be used to write a solution to Laplace’s equation as a boundary integral. Numerical models based on this approach are known as panel methods in the aerodynamics community. This paper introduces the availability of a computational tool for constructing numerical modelfor potential flow over an airfoil based on panel methods. Use of the software is illustrated by implementing a specific model using Hess and Smith panel method to compute the flow over a member of the NACA four-digit airfoils.

Keywords

Hess and Smith, Laplace equation, panel method, potential flow, NACA fourdigit.

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References

Anderson, John D., 1991, Fundamental o f Aerodynamics, 2nd ed., McGraw-Hill, Inc., Singapore.

Applied Computational Aerodynamics, Virginia Tech, online: http://www.dept.aoe.vt.edu/~mason/Mason_f/CAtxtChap4.pdf, (1998, February 24).

G. Dimitriadis, Panel Method, Universite de Liege, online: http://www.ltasaea.ulg.ac.be/cms/uploads/Aerodynamics04.pdf.

Hess-Smith Panel method, Universidad Politécnica de Madrid, online:http://canal.etsin.upm.es/CFDWORKSHOP/lect3-4.pdf, (2005, January 3).

J. Katz & A. Plotkin., 1991, Low-Speed Aerodynamics from Wing theory to Panel Methods,McGraw-Hill, Inc., Singapore.

Moran, J., 1984, An Introduction to Theoretical and Computational Aerodynamics, John Wiley & Sons, New York.

http://dx.doi.org/10.28989/angkasa.v8i1.131

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