As the velocity changes, the dynamic pressure changes and, according to Bernoulli's principle, the static pressure also changes.
It then speeds up again as it passes over or beneath the airfoil. The air approaching the leading edge of an airfoil is first slowed down. Taking an example, the NACA 24013 has a peak thickness of 13%, a design lift coefficient of 0.3, and the maximum camber located 20% behind the leading edge.Īt present, the resources available for computation allow the designers to design and optimize the airfoils specifically tailored to a particular application. The final two digits again indicate the maximum thickness in a percentage of chord.
The next two digits, when divided by 2, give the position of the maximum camber in tenths of the chord. The design lift coefficient (cL) is given by the first digit, when multiplied by 3/2, yields it in tenths. The NACA Five-Digit Series and the Four-Digit Series are quite similar as they use the same thickness forms, but the mean camber line is defined differently and the naming convention is a bit more complex. Using these values, one can compute the coordinates of the entire airfoil using specific equations, For example, the NACA 2415 airfoil has a maximum thickness of 15% with a camber of 2% located at 40% chord from the airfoil leading edge (or 0.4c). Here in, the maximum camber in the percentage of the chord (airfoil length) is given by the first digit, the second indicates the position of the maximum camber and lastly, the maximum thickness of the airfoil in the percentage of the chord is provided by the last two numbers. The family of airfoils which was curated by utilizing this approach was called the NACA Four-Digit Series. Also, the families, which included the 6-Series, were more complex shapes which were derived using theoretical methods. The Network of Aquaculture Centres in Asia-Pacific, airfoil series, the 4-digit, 5-digit, and the updated 4-/5- digit, were generated using analytical equations and analogies that described the curvature of the airfoil's mean-line (geometric centerline) as well as the section's thickness distribution along the length.
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