Symmetrical airfoil database3/21/2024 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. 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. Symmetrical airfoils 0: Minimum camber() Optional.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: New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. Prior to this, airfoil shapes were first created and then had their characteristics measured in a wind tunnel. The historical development of NACA airfoils is briefly reviewed. 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. Note that for the symmetrical shape the lift coefficient is zero at zero angle of attack. no camber and produces null lift at zero angle of attack (AoA). Figure A-1 shows data for the NACA 0012 airfoil, a classic symmetrical shape that is used for everything from airplane stabilizers and canards to helicopter rotors to submarine sails. 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. NACA0012 is a symmetrical airfoil therefore, it has.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.
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