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The equation for the camber line is split into sections either side of the point of maximum camber position (P).In order to calculate the position of the final airfoil envelope later the gradient of the camber line is also required.The equations are:

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The most obvious way to to plot the airfoil is to iterate through equally spaced values of x calclating the upper and lower surface coordinates.While this works, the points are more widely spaced around the leading edge where the curvature is greatest and flat sections can be seen on the plots.To group the points at the ends of the airfoil sections a cosine spacing is used with uniform increments of β

The forces that act upon an airfoil are measured in wind tunnels which provide straight and predictable airflow. A model airplane is supported by wires that lead to scales. These scales measure drag as well as front and rear lift.

Airfoil models are also unit tested in wind tunnels. They are built with small tubes running along many points of the foil that sit just under the surface. The tubes leave the model at a single point and are connected to a bank of manometer tubes. These tubes compare the pressures acting on the airfoil model to the reference point of atmospheric pressure. The different liquid levels in the manometer tubes give clear proof of the pressure values along the airfoil. These levels are photographed and mapped to a pressure curve. Now, a diagram can be made to show the positive and negative pressures relative to the angle of attack.

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