Calculations begin after selection of an airfoil. Airfoil coordinate data may be obtained in one of six ways:
The airfoil coordinate data may be manipulated by a control surface, modification of the airfoil's mean line, addition, or deletion of data points, and smoothing. 
After calculation have been completed, the airfoil coordinates, results, or graphical images may be saved. 
The default calculations are inviscid, In the viscous case, boundary layer calculations are performed and adjustments made to the lift and Pitch Coefficient values based on the viscous effects.
Reynolds Number 

Multiple Airfoils 
After calculations are complete:
Surface Velocity 
The Heading on all of the graphical displays will be identical. Some of the information is based on the calculation options and will only appear if the option is selected.
Line Number: