GOE 802 A AIRFOIL
Red line represents the mean camber line of the airfoil.
Yellow line represents the chord line.
Xcp (center of pressure) is calculated by the equation below:
x_cp = (0.25 + (CM /(CL *cos(alpha * pi / 180) + CD.*sin(alpha * pi / 180))))
Following plots are made on Matlab by using the data for highest and lowest Reynold
number and lowest Ncrit value for each in the list on the airfoil webpage.
Following figure shows the pressure distribution for GOE 802 A AIRFOIL for alpha = 0.