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Verified Commit ae585723 authored by Thomas Lambert's avatar Thomas Lambert :helicopter:
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feat(Rotor): add plotblade method

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src/classes/@Rotor/Rotor.m
+ 4
− 2
View file @ ae585723
......@@ -22,8 +22,9 @@ classdef Rotor < handle
% r0 - Non-dimensionalized root cutout, [-]
%
% Rotor methods:
% Rotor - Constructor
% plot - Plots the rotor in 3D
% Rotor - Constructor
% plot - Plots the rotor in 3D
% plotblade - Plots a single blade in 3D
%
% Rotor constructor:
% Rot = Rotor() creates an empty object.
......@@ -133,6 +134,7 @@ classdef Rotor < handle
% ---------------------------------------------
% Other methods
plot(self, varargin) % 3D plot of the rotor
plotblade(self, nSec, varargin) % Plot the blade
end
end
src/classes/@Rotor/plotblade.m 0 → 100644
+ 213
− 0
View file @ ae585723
function plotblade(self, nSec, varargin)
% PLOTBLADE 3D plot of a single blade.
% This method generates a 3D plot of the blade.
% If provided, it can also colorize the blade elements using some input data (e.g. cT, cP,
% dL, etc.).
% -----
%
% Syntax:
% Rot.plotblade() draws a 3D plot of a single blade with default colors.
%
% Rot.plotblade(nSec) specifies the number of sections to explicitely draw. If not specified,
% all sections will be drawned on top of the blade outline.
%
% Rot.plotblade(..., 'data', vector) draws the 3D of a single blade and colorize the sections
% using the values found in 'data'.
%
% Rot.plotblade(..., 'newFig', true) decide if plot should be on a new figure or on current
% axes (false by default).
%
% Rot.plotblade(..., surfProp, {Name, Value}) specifies the surface plot properties using one
% or more name-value pair arguments. See 'help surf' for a list of properties.
%
% Rot.plotblade(..., secProp, {Name, Value}) specifies the section plot properties using one
% or more name-value pair arguments. See 'help plot3' for a list of properties.
%
% Inputs:
% data : Vector to use for colorizing the blade elements (typically cT, cQ, etc).
% Size must be equal to Rot.Bl.nElem.
% nSec : Scalar corresponding to the number of sections to explicitely draw on top of the
% blade surface. If set to 0, all sections will be drawn.
%
% Outputs:
% 3D plot(s)
%
% Examples:
% Rot.plotblade()
% Rot.plotblade(5)
% Rot.plotblade('data', cT)
% Rot.plotblade('newFig', true)
% Rot.plotblade('surfProp', {'FaceAlpha', 1, 'FaceColor','blue'})
% Rot.plotblade('secProp', {'LineWidth', 1, 'LineStyle','--'})
%
% See also: rotor, rotare, template.
%
% <a href="https://gitlab.uliege.be/rotare/documentation">Complete documentation (online)</a>
% ----------------------------------------------------------------------------------------------
% (c) Copyright 2022-2023 University of Liege
% Author: Thomas Lambert <t.lambert@uliege.be>
% ULiege - Aeroelasticity and Experimental Aerodynamics
% MIT License
% Repo: https://gitlab.uliege.be/rotare/rotare
% Docs: https://gitlab.uliege.be/rotare/documentation
% Issues: https://gitlab.uliege.be/rotare/rotare/-/issues
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
import af_tools.formatairfoilcoord
% Defaults and Constants
DEF.N_SEC = 0; % All sections by default
DEF.AF_POINTS = 31; % Plot 30 points per airfoil
DEF.PITCH_AXIS = 0.25; % Blades are pitched according to the quarter-chord
DEF.CHORD_SPACING_RULE = 'halfcosine';
if nargin < 2
nSec = 0;
end
% Determine indexes of sections to be plotted
if nSec == 0 || nSec >= length(self.Bl.r)
iSec = 1:1:length(self.Bl.r);
else
iSec = floor(linspace(1, length(self.Bl.r), nSec));
end
% Input validation
valData = @(x) validateattributes(x, {'numeric'}, ...
{'row', 'nonempty', 'numel', length(self.Bl.chord)});
valLogi = @(x) validateattributes(x, {'logical'}, {'scalar'});
% valPlotOpts = @(x) validateattributes(x, {'logical'}, {'scalar'}); % FIXME
p = inputParser;
p.FunctionName = 'plot';
addOptional(p, 'data', zeros(size(self.Bl.chord)), valData);
addOptional(p, 'newFig', false, valLogi);
addOptional(p, 'surfProp', {});
addOptional(p, 'secProp', {});
parse(p, varargin{:});
data = p.Results.data;
newFig = p.Results.newFig;
surfProp = p.Results.surfProp;
secProp = p.Results.secProp;
% -------------------------------------------
% Normalize airfoil coordinates so they all have the same X components and number of points
coords = normalizeafcoord(self, DEF);
% Create matrices to scale and apply color appropriately
chordMat = repmat(self.Bl.chord, length(coords(:, 1)), 1);
dataMat = repmat(data, length(coords(:, 1)), 1);
% Scale elements and twist them properly to create the correct blade
Blade = gettrueposition(self.Bl, coords, chordMat, DEF);
% Plot blade and rotor
if newFig
figname = 'Single Blade';
figure('PaperUnits', 'inches', 'PaperPosition', [0 0 1280 1024] / 250, 'Name', figname);
hAx = axes('NextPlot', 'add');
else
hAx = axes;
end
bladeplot(Blade, dataMat, hAx, iSec, surfProp, secProp);
if newFig
setgca();
end
end
% --------------------------------------------------------------------------------------------------
function coords = normalizeafcoord(self, DEF)
% NORMALIZEAFCOORD Normalizes airfoil coordinates
% This ensures all airfoils will share the same X coordinates and number of points
% and simplifies further drawings
import af_tools.utils.spacedvector
% Get a vector for chordwise positions
xpts = spacedvector(DEF.CHORD_SPACING_RULE, DEF.AF_POINTS);
xpts = xpts(:); % Ensure it is a column vector
% Interpolate Y coordinate for all airfoils on the new points
ypts = zeros(DEF.AF_POINTS * 2 - 1, length(self.Af));
for i = 1:length(self.Af)
yptsUp = interp1(self.Af(i).upper(:, 1), self.Af(i).upper(:, 2), flipud(xpts));
yptsLow = interp1(self.Af(i).lower(:, 1), self.Af(i).lower(:, 2), xpts);
ypts(:, i) = [yptsUp; yptsLow(2:end)];
end
% Combine the new coordinates in a single array
xpts = [flipud(xpts); xpts(2:end)];
coords = [xpts, ypts];
end
function Blade = gettrueposition(Elem, coords, chordMat, DEF)
% GETTRUEPOSITION Returns the true position of the blade elements after scaling and twisting
% Scale the blade to actual chord and span
geomX = repmat(coords(:, 1) - DEF.PITCH_AXIS, 1, length(Elem.chord)) .* chordMat;
geomY = repmat(Elem.y, length(coords(:, 1)), 1);
geomZ = zeros(size(geomX));
for i = 1:length(Elem.chord)
geomZ(:, i) = coords(:, 1 + Elem.iAf(i)) .* chordMat(:, i);
end
% Pitch the airfoil according to the correct local twist angle
for i = 1:length(Elem.chord)
rotY = roty(rad2deg(Elem.twist(i)));
dummy = rotY * [geomX(:, i), geomY(:, i), geomZ(:, i)]';
Blade.x(:, i) = dummy(1, :);
Blade.y(:, i) = dummy(2, :);
Blade.z(:, i) = dummy(3, :);
end
end
function bladeplot(Blade, dataMat, handleAxis, iSec, surfProp, secProp)
% PLOTBLADE Plot a single blade (color surface + outline)
DEF_SURFACE_PROP = {'EdgeColor', 'none', 'FaceAlpha', 0.3};
DEF_SECTION_PROP = {'Color', 'k'};
if isempty(surfProp)
surfProp = DEF_SURFACE_PROP;
end
if isempty(secProp)
secProp = DEF_SECTION_PROP;
end
surf(Blade.x, Blade.y, Blade.z, dataMat, 'Parent', handleAxis, surfProp{:});
hold on;
plot3(Blade.x(:, iSec), Blade.y(:, iSec), ...
Blade.z(:, iSec), 'Parent', handleAxis, secProp{:});
end
function setgca()
% SETGCA Sets axes options for all plots
view(3);
grid on;
axis equal;
% hCol=colorbar;
% hCol.Label.String = 'Sectional thrust, dT [N]';
set(gca, 'FontName', 'Helvetica');
set(gca, 'Fontsize', 14);
set(gca, ...
'Box', 'off', ...
'TickDir', 'out', ...
'TickLength', [.02 .02], ...
'XMinorTick', 'off', ...
'YMinorTick', 'off', ...
'YGrid', 'on', ...
'XGrid', 'on', ...
'XColor', 'k', ...
'YColor', 'k', ...
'GridLineStyle', ':', ...
'GridColor', 'k', ...
'GridAlpha', 0.25, ...
'LineWidth', 1);
set(gcf, 'PaperPositionMode', 'auto');
end
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