P = rem( floor( n / 100), 10)/ 10 % Location of maximum camber (2nd digit) M = floor( n / 1000)/ 100 % Maximum camber (1st digit)
TEARDROP AIRFOIL GENERATOR 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 % This function generates a set of points containing the coordinates of a
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