This utility predicts the flow over NACA 4 and 5-digit airfoils using an incompressible panel method. The surface pressure distribution and surface coordinates are presented for the airfoil, angle-of-attack and number of panels that you specify. Click on the first link to use the panel code. Follow the other links below for more information about the theory and use of the code, and for an explanation of the numerical coding of NACA 4 and 5 digit airfoils.

• Open the Panel Code Window
• About the utility
• View/download the source code
• Deciphering the NACA 4 and 5-digit airfoil series