my point here is that this is freely available information, all the airfoil programs do is translate the points into a.
In the paper special attention is given to wind tunnel blockage corrections of the measurements, and also to the estimation of the accuracy of the measured quantities. The key with Inventor, at least, is to trim out a whole pile of the coordinates to make a spline that doesnt take up a huge amount of memory. The experimental results are also compared with published results wherever they are available(4). The wake survey gives an accurate estimation of the zero lift drag coefficient which is of vital importance in the operational characteristics of the airfoil in windgenerators. These coefficients are subsequently compared to those obtained from balance measurements.
The following s tudy compares Simulation CFD results for lift and drag against two sets of test data for the NACA 0012 airfoil, one of the most tested of the airfoils McCroskey. The pressure distribution over the airfoil with the angle of attack shows clearly the flow regimes over the airfoil (separated or unseparated) and their integration leads to the calculation of the force and moment coefficients. Many NACA airfoils have been physically tested and have extensive data use in evaluation of advanced Computational Fluid Dynamics codes. The measurements which are taken refer to pressure distribution over the airfoil using a scannivalve and to airfoil coefficients using a six component balance from 0 to 180 degrees angle of attack, as well as to wake surveys at small angles of attack. Wind tunnel tests were conducted on a NACA 0012 two dimensional airfoil.