With a manual editing tool you can create an aerofoil geometry that has been constructed elsewhere. The required input for the process is the name of the section file containing the coordinates of the aerofoil that you have already produced. This should be an ASCII data file with the extension ".txt". Store the section in a relevant location for later use in the wind tunnel.
 

Sample of Required Format : 
Section : 0012
Number of Data Points = 61.0000
Span = 10.0
Upper Surface	Lower Surface
X         Y         X         Y
0         0         0         0
0.002739 	0.0091145	0.002739	-0.0091145
0.010926	 0.017770	 0.010926	-0.017770
0.024472	 0.025893	 0.024472	-0.025893
0.043227	 0.033389	 0.043227	-0.033389
0.066987	 0.040145	 0.066987	-0.040145
            .....
0.98907		 0.0027828	0.98907		-0.0027828
0.99726		 0.0016437	0.99726		-0.0016437
1.0000		  0.0012600	1.0000	 	-0.0012600

Notes : Section name should contain letters and numbers only (no spaces).
File must contain span of wing in metres on line 3 or the text "Span = 2D"
Must contain number of surface data points supplied on line 2
Section surface data points (meters) are listed as X,Y cordinates, starting at leading edge and running along upper and lower surfaces to trailing edge. (leading edge point will be a duplicate). The file format must be identical to that produced by the NACA milling machine otherwise it will not suit the balance mounting system and cannot be installed into the tunnel.


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