Sym = 2 % Comprovation of symetric airfoil with one 0 Sym = 1 % Comprovation of symetric airfoil with two 0 P = rem( floor( n / 100), 10)/ 10 % Location of maximum camber (2nd digit) M = floor( n / 1000)/ 100 % Maximum camber (1st digit)
#NACA AIRFOIL GENERATOR 6 SERIES#
%- MEAN CAMBER 4 DIGIT SERIES CALCULATION. ^ 4) % Thickness y coordinate with opened trailing edge ^ 4) % Thickness y coordinate with closed trailing edge Y_c = zeros( 1, s) % Mean camber vector prelocationĭyc_dx = zeros( 1, s) % Mean camber fisrt derivative vector prelocation T = rem( n, 100)/ 100 % Maximum thickness as fraction of chord (two last digits)Īlpha = alpha / 180 * pi % Conversion of angle of attack from degrees to radians X =( 1 - cos( beta))/ 2 % X coordinate of airfoil (cosine spacing) X = linspace( 0, 1, s) % X coordinate of airfoil (linear spacing)īeta = linspace( 0, pi, s) % Angle for cosine spacing S = 1000 % Default number of points value % y_i -> Intrados y coordinate of airfoil vector (m)įunction= NACA( n, alpha, c, s, cs, cte) % y_e -> Extrados y coordinate of airfoil vector (m) % x_i -> Intrados x coordinate of airfoil vector (m) % x_e -> Extrados x coordinate of airfoil vector (m) % cte -> Opened or closed trailing edge (0 or 1 respectively) (0 default) % cs -> Linear or cosine spacing (0 or 1 respectively) (1 default) % s -> Number of points of airfoil (1000 default) % c -> Chord of airfoil (m) (1 m default) % alpha -> Angle of attack (º) (0º default) % It also plots the airfoil for further comprovation if it is the required % opened or closed trailing edge and the angle of attack of the airfoil. % to be calculated, spacing type (between linear and cosine spacing), % its number and, as additional features, the chordt, the number of points % NACA airfoil from the 4 Digit Series, 5 Digit Series and 6 Series given
#NACA AIRFOIL GENERATOR 6 GENERATOR#
NACA 4 series aerofoil generator - R6.gh (19.% This function generates a set of points containing the coordinates of a I’ve also used Fit Curve on the Mean Line to smooth out the bump that inevitably occurs with Abbot and von Doenhoff’s method, and the Flow component to map the Thickness Distribution onto the Mean Line: a lot less fuss than using the mathematical approach that was necessary in the 1930s! I’ve improved on the methods desribed 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 at the critical Leading Edge, as well as wrapping the Thickness Distribution 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. Although the 4 series aerofoils are rather old (they were developed in the thirties) they are still useful for low-speed applications such as wind turbines or velomobile fairings. A NACA series 4 aerofoil generator, based on the equations and methods set out in Abbot and von Doenhoff’s classic student aerodynamicists’ text, Theory of Wing Sections.