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4 digit airfoil generator
4 digit airfoil generator











4 digit airfoil generator

#% K1 constant calculation by interpolation #% R constant calculation by interpolation Rn = int( series) #% Type of camber (3rd digit) #% Location of maximum camber (2nd digit)

4 digit airfoil generator series#

#%- MEAN CAMBER 5 DIGIT SERIES CALCULATION. If p = 0: sym = 1 # % Comprovation of symetric airfoil with two 0Įlse: sym = 2 #% Comprovation of symetric airfoil with one 0

4 digit airfoil generator

#%- MEAN CAMBER 4 DIGIT SERIES CALCULATION. If cte = 1: #% Thickness y coordinate with closed trailing edge Y_c = zeros( s) #% Mean camber vector prelocationĭyc_dx = zeros( s) #% Mean camber fisrt derivative vector prelocation #% Maximum thickness as fraction of chord (two last digits)Īlpha_deg = alpha #% Angle of attack - degreesĪlpha = alpha / 180 * pi #% Conversion of angle of attack from degrees to radians X = ( 1.0 - 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 Nc = len( series) #%number of digits (4, 5, 6) # % y_i -> Intrados y coordinate of airfoil vector (m)įrom numpy import pi, sin, cos, tan, arctan, log, sign, linspace, zeros, appendĭef NACA( series, alpha = 0.0, c = 1.0, s = 200, cs = 1, cte = 0):

4 digit airfoil generator

# % y_e -> Extrados y coordinate of airfoil vector (m) # % x_i -> Intrados x coordinate of airfoil vector (m)

4 digit airfoil generator

# % 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) # % series -> NACA number (4, 5 or 6 digits) # % 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 #% Copyright (c) 2016 Alejandro de Haro (original - matlab code)













4 digit airfoil generator