Here is the NACA 4, 5, and 6 series airfoil generator from the PDAS site. I compiled it and created an input file for the NACA 65A009. This is an update to the code I posted previously from their site. It has about half as much error as the older version. However, it is still a substantial amount of error (max. of 2.28% for the new version compared to 5% for the old version). I wouldn't recommend using this code for the 6 series. I'm providing it here for anyone interested.

The updated code is a lot more convenient to use than the older version. It outputs to gnuplot rather than a postscript file. The output matches the coordinate locations of the original data sheet which is nice. I included all of the example input files that the author included in a different folder. I have a comparison file in there comparing the NACA 65A009 data points from the code to those of the original document.

Anthony

update; have since determined it is best to use the data points from NACA RM L51I12 for the 65A009 definition.