All computational computer work was performed on a high-speed Unix computer. Specifically, it runs freeBSD 5.4_STABLE for the AMD64 processors. A C++ program that determines the coefficient of pressure on every panel of a body was written and compiled with the gcc/g++ compiler.
A script utilizing the GnuPlot graphing software was also written that constructed airfoil previews from just the data points. Approximately one thousand airfoils were briefly previewed.
Figure 2. The airfoil files contain points in a 2 dimensional plane. Shown above are the points graphed for the NACA 2412 airfoil.
Figure 3.The NACA 2412 airfoil shown in figure 2, but with the points connected by lines, forming a smooth airfoil.
As it was, this particular airfoil caused the analyzing program problems, so a slightly modified airfoil was used as the "NACA 2412". The minor difference cannot be seen without an incredibly high-resolution image under vast magnification. For all intents and purposes it is exactly the same.
Next: Results and Analysis
© 2006 Nic Reveles