+af_tools/+utils/spacedvector.m

 function vect = spacedvector(spacing, nPoints)
     % SPACEDVECTOR Returns a vector based on chosen spacing and number of points
+    %
+    % Spacing:
+    %   - linear     : points spaced linearily
+    %   - halfcosine : more dense at beginning and end of vector
+    %   - cosine     : more dense at the beginning and more spaced out at the end
+    %   - sine       : more dense at the end and more spaced out at the beginning
+    %
     % -----
-    % (c) Copyright 2022 University of Liege
+    % (c) Copyright 2022-2023 University of Liege
     % Author: Thomas Lambert <t.lambert@uliege.be>
     % ULiege - Aeroelasticity and Experimental Aerodynamics
     % Apache 2.0 License
@@ -18,6 +25,9 @@ function vect = spacedvector(spacing, nPoints)
         case 'cosine'
             beta = linspace(0, pi / 2, nPoints);
             vect = 1 - cos(beta);
+        case 'sine'
+            beta = linspace(0, pi / 2, nPoints);
+            vect = sin(beta);
     end
 
 end

+af_tools/@Polar/Polar.m

@@ -145,7 +145,7 @@ classdef Polar < handle
             %
             % See also: af_tools.findcllinearrange.
 
-            [self.Lin.clRange, self.Lin.aoaRange, self.Lin.slope] = ...
+            [self.Lin.aoaRange, self.Lin.clRange, self.Lin.slope] = ...
                 af_tools.findcllinearrange(self);
         end
 

+af_tools/nacacamber.m

@@ -6,13 +6,13 @@ function [coord, gradY] = nacacamber(varargin)
     % -----
     %
     % Usage:
-    %   [X, Y] = NACACAMBER prompts the user for the airfoil digits, then calculates the coordinates
-    %   of the camberline using 100 points spaced with the half-cosine rule.
+    %   [coord, gradY] = NACACAMBER prompts the user for the airfoil digits, then calculates the
+    %   coordinates of the camberline using 100 points spaced with the half-cosine rule.
     %
-    %   [X, Y] = NACACAMBER(DIGITS) calculates the coordinates of the camberline for the NACA
-    %   airfoil specified by DIGITS, without further input.
+    %   [coord, gradY] = NACACAMBER(DIGITS) calculates the coordinates of the camberline for the
+    %   NACA airfoil specified by DIGITS, without further input.
     %
-    %   [X, Y] = NACACAMBER(DIGITS, NPOINTS) calculates the coordinates of the NACA airfoil
+    %   [coord, gradY] = NACACAMBER(DIGITS, NPOINTS) calculates the coordinates of the NACA airfoil
     %   specified by DIGITS, using NPOINTS points spaced with the half-cosine rule.
     %
     %   [...] = NACACAMBER(..., 'spacing', SP) uses the defined spacing rule to determine to
@@ -20,14 +20,14 @@ function [coord, gradY] = nacacamber(varargin)
     %     'linear'     - linear
     %     'halfcosine' - (default) finer at leading and trailing edges
     %     'cosine'     - finer at leading edge, coarser at the trailing edge
+    %     'sine'       - finer at trailing edge, coarser at the leading edge
     %
     % Inputs:
     %   digits  : Character vector representing the NACA airfoil (ex: '0012', '24120', '24012')
     %   nPoints : Number of output coordinates
     %
     % Output:
-    %   xc : Camberline X coordinates (0 <= X <= 1)
-    %   yc : Camberline Y coordinates
+    %   coord : Camberline coordinates [nPts x 2]
     %   gradY : Gradient of Y (required to get the whole airfoil coordinates)
     %
     % Example:
@@ -41,7 +41,7 @@ function [coord, gradY] = nacacamber(varargin)
     % <a href="https://gitlab.uliege.be/am-dept/matlab_airfoil_toolbox">Documentation (online)</a>
 
     % -------------------------------------------
-    % (c) Copyright 2022 University of Liege
+    % (c) Copyright 2022-2023 University of Liege
     % Author: Thomas Lambert <t.lambert@uliege.be>
     % ULiege - Aeroelasticity and Experimental Aerodynamics
     % MIT License