![]() The coordinates give smooth inviscid velocity distributions, but some of Von Doenhoff) courtesy of Ralph Carmichael, PDAS: Corrected NACA coordinates from Theory of Airfoil Sections (Abbott and.NACA Report 93 (1921) includes coordinates and wind tunnel data on.Model airplane site, mostly focused on flying wings:.Martin Hepperle's site, including airfoil coordinates (mostly listed here as well) and lots.The TraCFoil website has many airfoils that are not included below. TraCFoil airfoil and rib plotting program for models:.Includes many nice features for plotting airfoils and comparing Creates an IGES file from airfoil coordinates.Īirfoils aggregated from many sources (as of ). IGES: Online CAD/CAM NURBS tool from Flusur.The plug-in can be installed via the Rhino Package Manager per: ![]() With Rhino 7 or newer and Rhino for Mac V7 or newer, Rhino Plug-In for importing airfoils into CAD/CAM NURBS.In addition to the links below, more airfoil-info links can be found back at the UIUC Airfoil Data Site homepage.The Incomplete Guide to Airfoil Usage: A useful aircraft/airfoil "reverse lookup" database from David Lednicer.The airfoils are listed alphabetically by the airfoil filename (which is usually close to the airfoil name).Īnswers to frequently asked questions are posted UIUC Airfoil Data Site gives some background The airfoil is described using six digits in the following sequence:įor example, the NACA 61 2-315 a=0.5 has the area of minimum pressure 10% of the chord back, maintains low drag 0.2 above and below the lift coefficient of 0.3, has a maximum thickness of 15% of the chord, and maintains laminar flow over 50% of the chord.įurther advancement in maximizing laminar flow achieved by separately identifying the low pressure zones on upper and lower surfaces of the airfoil.Included below are coordinates for approximately 1,600 airfoils (Version 2.0). Two digits describing the maximum thickness in percent of chord.įor example, the NACA 16-123 airfoil has minimum pressure 60% of the chord back with a lift coefficient of 0.1 and maximum thickness of 23% of the chord.Īn improvement over 1-series airfoils with emphasis on maximizing laminar flow.One digit describing the lift coefficient in tenths.One digit describing the distance of the minimum pressure area in tens of percent of chord.The 1-series airfoils are described by five digits in the following sequence: Prior to this, airfoil shapes were first created and then had their characteristics measured in a wind tunnel. In addition, for a more precise description of the airfoil all numbers can be presented as decimals.Ī new approach to airfoil design pioneered in the 1930s in which the airfoil shape was mathematically derived from the desired lift characteristics. One digit describing the distance of maximum thickness from the leading edge in tens of percent of the chord.įor example, the NACA 1234-05 is a NACA 1234 airfoil with a sharp leading edge and maximum thickness 50% of the chord (0.5 chords) from the leading edge.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.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. The NACA four-digit wing sections define the profile by: 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. 1.2 The equation for a cambered 4-digit NACA airfoil.1.1 Equation for a symmetrical 4-digit NACA airfoil.
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