AERODYNAMIC CHARACTERISTICS OF AIRFOIL USING PANEL METHOD

Buyung Junaidin

Submitted : 2017-08-31, Published : .

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.

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