![]() ![]() The leading edge approximates a cylinder with a chord-normalized radius of to −0.1036) will result in the smallest change to the overall shape of the airfoil. If a zero-thickness trailing edge is required, for example for computational work, one of the coefficients should be modified such that they sum to zero. In this equation, at x = 1 (the trailing edge of the airfoil), the thickness is not quite zero. T = maximum thickness as a fraction of the chord (so t gives the last two digits in the NACA 4-digit denomination divided by 100). He half thickness at a given value of x (centerline to surface), X = position along the chord from 0 to 1.00 (0 to 100%), The formula for the shape of a NACA 00xx foil, with "xx" being replaced by the percentage of thickness to chord y t = 5 t 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. Last two digits describing maximum thickness of the airfoil as percent of the chord.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.Second digit describing the distance of maximum camber from the airfoil leading edge in tenths of the chord.First digit describing maximum camber as percentage of the chord.The NACA four-digit wing sections define the profile by: The parameters in the numerical code can be entered into equations to precisely generate the cross-section of the airfoil and calculate its properties. The shape of the NACA airfoils is described using a series of digits following the word "NACA". The NACA airfoils are airfoil shapes for aircraft wings developed by the National Advisory Committee for Aeronautics (NACA). Each airfoil data bank computer code was written to be used on the Amdahl Computer system, which is IBM compatible and uses Fortran.Related Resources: calculators NACA Airfoil Plotter and Equations The various component of each computer code, the source of the data used to create the airfoil data bank, the limitations of each data bank, program listing, and a sample case with its associated input-output are described. ![]() The families chosen consisted of the Clark-Y, NACA 16 series, and NACA 4 digit series airfoils. ![]() Realizing the need for such data, a study was initiated to provide airfoil data banks for three commonly used airfoil families in propeller design and analysis. Inherent in the majority of the theoretical performance models to date is the need for airfoil data banks which provide lift, drag, and moment coefficient values as a function of Mach number, angle-of-attack, maximum thickness to chord ratio, and Reynolds number. Aerodynamic data banks for Clark-Y, NACA 4-digit and NACA 16-series airfoil families With the renewed interest in propellers as means of obtaining thrust and fuel efficiency in addition to the increased utilization of the computer, a significant amount of progress was made in the development of theoretical models to predict the performance of propeller systems.
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