**Last Updated: 6/15/2018**

**Panel
Method Spreadsheet (Updated 6/15/2018)**

This workbook implements the vortex panel method for a 2D
airfoil. The algorithm is
from Kuethe and Chow, *Foundations of Aerodynamics*, 4^{th} Edition, Wiley
(1986). Detailed
implementation instructions are provided in a separate pdf file. Inputs are coordinate data for the
airfoil (from a source such as Abbott and von Doenhoff,
*Theory of Wing Sections*, Dover (1959)
and the angle of attack. This being an inviscid flow calculation,
the flow will remain attached for any angle of attack. The calculation returns the
pressure coefficient C_{p} as a function of
position and a streamline plot. The
student can use these local results to compute the section lift coefficient,
etc.

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