...
The process for calculating camber comes from “The Winning Solar Car”.
Identify the specifications for a symmetric airfoil with superior drag characteristics and good optimization for laminar boundary layer length
Identify the point of max thickness, use this to record Xmax, the x coordinate of this point where x=0 is at the tip of the frontmost portion of the aerobody
Apply this formula to various points along the aerobody
This formula denotes the shift upward of the centerline at the X. C% is the desired camber and should be within 2%-5% for improved aerodynamic properties.