![naca 6 digit airfoil generator naca 6 digit airfoil generator](https://image.slidesharecdn.com/naca4-digitdelta-110913101028-phpapp02/95/naca-4-digitdelta-2-728.jpg)
Some of the six-digit aerofoils are more tolerant to production variation as compared to typical five-digit aerofoils. However, the drag bucket seen in wind-tunnel test results may not show up in actual flight.
#NACA 6 DIGIT AIRFOIL GENERATOR SERIES#
Their low-speed characteristics behave like the four – and five-digit series but show much better high-speed characteristics. This was achieved by placing the maximum thickness far back from the LE. The six-digit series aerofoils were generated from a more or less prescribed pressure distribution and were designed to achieve some laminar flow. The NACA six-digit series aerofoil came much later (it was first used for the P51 Mustang design in the late 1930s) from the need to generate a desired pressure distribution instead of being restricted to what the relatively simplistic four – and five-digit series could offer. The state-of-the-art for a good aerofoil often follows reverse engineering – that is, it attempts to fit a cross-sectional shape to a given pressure distribution. The five-digit family was an improvement over the four-digit NACA series aerofoil however, researchers subsequently found better geometric definitions to represent a new family of a six-digit aerofoil. Position in % maximum camber in 1: inverted are maximum t/cĬhord 1/10 of chord cube ratio in % of chord Maximum camber Maximum thickness of 0: straight, the last two digits Following are the examples of the NACA 23015 and NACA 23115: The NACA five-digit aerofoil has more curvature toward the LE. The middle digit has only two options: 0 for a straight and 1 for an inverted cube. The middle digit represents the aft position of the mean line, resulting in the change in the defining camber line curvature. The first two and the last two digits represent the same definitions as in the four-digit NACA aerofoil.