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One digit describing the roundness of the leading edge with 0 being sharp, 6 being the same as the original airfoil, and larger values indicating a more rounded leading edge.
Naca airfoil generator 6 code#
The following table presents the various camber line profile coefficients:įour- and five-digit series airfoils can be modified with a two-digit code preceded by a hyphen in the following sequence: The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord, is: y t = 5 t c , Plot of a NACA 0015 foil, generated from formula The 15 indicates that the airfoil has a 15% thickness to chord length ratio: it is 15% as thick as it is long.Įquation for a symmetrical 4-digit NACA airfoil The NACA 0015 airfoil is symmetrical, the 00 indicating that it has no camber. Four-digit series airfoils by default have maximum thickness at 30% of the chord (0.3 chords) from the leading edge. įor example, the NACA 2412 airfoil has a maximum camber of 2% located 40% (0.4 chords) from the leading edge with a maximum thickness of 12% of the chord. Last two digits describing maximum thickness of the airfoil as percent of the chord.Second digit describing the distance of maximum camber from the airfoil leading edge in tens of percents of the chord.First digit describing maximum camber as percentage of the chord.The NACA four-digit wing sections define the profile by: 1.2 Equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.Finally, a Flow component was used to map the Thickness Distribution onto the Mean Line: a lot less fuss than using the mathematical approach that was necessary in the 1930s! The Mean Line was cleaned up by running it through a Fit Curve component, to smooth out the bump that inevitably occurs (with Abbot and von Doenhoff’s method) when the equation for the front portion and rear portion of the Mean Line meet. I’ve improved on the methods described in the book by using Cosine spacing of the samples along the Thickness Distribution, working from Trailing Edge to Leading Edge so that there are more samples in the critical Leading Edge area, as well as wrapping it around the Mean Line as a single curve from Trailing Edge to Trailing Edge. They are also tolerant of innacuracies in construction, dirt and insect accumulation, and real-world conditions generally.
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NACA's 4 series aerofoils are now rather old (they were developed in the thirties), but they are still useful for low-speed applications such as wind turbines or velomobile fairings.
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It's based on the equations and methods set out in Abbot and von Doenhoff’s classic student aerodynamicists’ text, Theory of Wing Sections. I've been playing around in Rhino 6 recently, and put together a GH definition to generate NACA series 4 aerofoils. This has already been posted on the GH forum, but I suppose it should have gone here instead -)