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Verified Commit 55dff5ca authored by Thomas Lambert's avatar Thomas Lambert :helicopter:
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feat(plots): add static and semi flap plots

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utils/analysis/plotstatictests.m 0 → 100644
+ 128
− 0
View file @ 55dff5ca
function ParsedDat = plotstatictests(StatData)
% PLOTSTATICTESTS Plot CL and CD for each set of wing w.r.t front and aft dihedral
% Todo
% ----------------------------------------------------------------------------------------------
% (c) Copyright 2022 University of Liege
% Author: Thomas Lambert <t.lambert@uliege.be>
% ULiege - Aeroelasticity and Experimental Aerodynamics
% MIT License
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
close all;
% Constants and defaults
CHORD = 0.05;
SPAN = 2 * 0.2;
C_TO_K = 273.15;
AIRSPEEDS = [5, 8, 10, 14];
% Create useful vectors for each sets of front/aft position
% Vectors dimensions = number of speeds
% First we get all unique angles for front and aft wings that were tested
for i = numel(StatData):-1:1
angleF(i) = StatData(i).Front.angles(1);
angleA(i) = StatData(i).Aft.angles(1);
end
angleF = unique(angleF);
angleA = unique(angleA);
nVeloc = numel(StatData) / (length(angleF) * length(angleA)); % Number of velocities per config
% Create base mesh grid for all tests cases
[gridF, gridA] = meshgrid(angleF, angleA);
% Initialize force coefficients in X and Y for Front and Aft
cfzF = zeros([size(gridF), nVeloc]);
cfxF = zeros([size(gridF), nVeloc]);
cfzA = zeros([size(gridF), nVeloc]);
cfxA = zeros([size(gridF), nVeloc]);
stdfz = zeros([size(gridF), nVeloc]);
for i = 1:numel(StatData)
idx1 = gridF == StatData(i).Front.angles(1) & gridA == StatData(i).Aft.angles(1);
[~, idx2] = min(abs(AIRSPEEDS - StatData(i).Testcase.airspeed));
for iPos = {'Front', 'Aft'}
pos = string(iPos);
fz = mean(StatData(i).(pos).forces(:, 3));
fx = mean(StatData(i).(pos).forces(:, 1));
% stdfz = std(StatData(i).(pos).forces(:, 3));
% stdfx = std(StatData(i).(pos).forces(:, 1));
dens = airdensity(StatData(i).Testcase.temp + C_TO_K, ...
StatData(i).Testcase.press);
speed = StatData(i).Testcase.airspeed;
cfz = forcetocoeff(fz, dens, speed, CHORD, SPAN, 'force');
cfx = forcetocoeff(fx, dens, speed, CHORD, SPAN, 'force');
% Nondim with projected area
cfz = cfz / sind(90 + StatData(i).(pos).angles(1));
cfx = cfx / sind(90 + StatData(i).(pos).angles(1));
if strcmp(pos, 'Front')
cfzF(:, :, idx2) = cfzF(:, :, idx2) + idx1 * fz;
cfxF(:, :, idx2) = cfxF(:, :, idx2) + idx1 * fx;
cfzF(:, :, idx2) = cfzF(:, :, idx2) + idx1 * fz;
cfxF(:, :, idx2) = cfxF(:, :, idx2) + idx1 * fx;
else
cfzA(:, :, idx2) = cfzA(:, :, idx2) + idx1 * fz;
cfxA(:, :, idx2) = cfxA(:, :, idx2) + idx1 * fx;
end
end
end
ParsedDat.cfzF = cfzF;
ParsedDat.cfxF = cfxF;
ParsedDat.cfzA = cfzA;
ParsedDat.cfxA = cfxA;
for i = 1:nVeloc
figure('Name', ['V=', i]);
ax1 = subplot(221); % Front CL
surf(gridF, gridA, cfzF(:, :, i));
setgca();
ax2 = subplot(222); % Front CD
surf(gridF, gridA, cfxF(:, :, i));
setgca();
ax3 = subplot(223); % Aft CL
surf(gridF, gridA, cfzA(:, :, i));
setgca();
ax4 = subplot(224); % Aft CD
surf(gridF, gridA, cfxA(:, :, i));
setgca();
% linkprop([ax1 ax3], 'Zlim'); % CL plots
% linkprop([ax2 ax4], 'Zlim'); % CD plots
end
for i = 1:length(angleF)
figure;
size(angleA);
size(cfzF(i, :, 4));
hold on;
title([angleF(i)]);
errobar(angleA, cfzF(:, i, 3), stdfzF(:, i, 3), '-o');
plot(angleA, cfzF(:, i, 3), '-o');
plot(angleA, cfzA(:, i, 3), '-o');
plot(angleA, cfzF(:, i, 3) + cfzA(:, i, 3), '--x');
hold on;
end
end
function setgca()
% SETGCA Sets the axes parameters
xlabel('Front');
ylabel('Aft');
grid on;
end
utils/plotsemiflap.m 0 → 100644
+ 418
− 0
View file @ 55dff5ca
function ResData = plotsemiflap(type)
% PLOTWINDONON Plots the forces in wind on and wind off conditions
% Todo
% ----------------------------------------------------------------------------------------------
% (c) Copyright 2022 University of Liege
% Author: Thomas Lambert <t.lambert@uliege.be>
% ULiege - Aeroelasticity and Experimental Aerodynamics
% MIT License
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
set(0, 'defaulttextinterpreter', 'latex');
POSITION = 'Front';
INTERESTING_POINTS = [
];
PLOT_TIME = true;
SAVE_TIKZ_PARAM = []; % INTERESTING_POINTS(1:2, :);
MYGREY = [186, 216, 221] / 255;
ALLPLOTS = false;
SAMPLING = 1000;
ERR_CAPSIZE = 3;
CHORD = 0.05;
SPAN = 2 * 0.2;
C_TO_K = 273.15;
switch type
case 'Front' % Front wing is flapping
dat3cm = '2022-3cm-flapFront.mat';
dat5cm = '2022-5cm-flapFront.mat';
notType = 'Aft';
case 'Aft' % Aft wing is flapping
dat3cm = '2022-3cm-flapAft.mat';
dat5cm = '2022-5cm-flapAft.mat';
notType = 'Front';
end
Tmp = load(['data/cleaned_MAT/2022/', dat3cm]);
ResData(1, :) = Tmp.ExpData;
Tmp = load(['data/cleaned_MAT/2022/', dat5cm]);
ResData(2, :) = Tmp.ExpData;
% Remove useless data
ResData = rmfield(ResData, {'arduStart', 'tunnelStart'}); % Useless
% FIXME: remove deprecated
ResData = rmfield(ResData, {'arduFile', 'tunnelFile', ...
'dx', 'airspeed', 'freq'});
for i = 1:size(ResData, 1)
% for i = 1
for j = 1:size(ResData, 2)
dens = airdensity(ResData(i, j).Testcase.temp + C_TO_K, ...
ResData(i, j).Testcase.press);
speed = ResData(i, j).Testcase.airspeed;
% Calculate main frequency
ResData(i, j).(type).trueFreq = getmainfrequency(ResData(i, j).(type).angles, ...
1 / diff(ResData(i, j).time(1:2)));
ResData(i, j).(notType).trueFreq = 0;
% Calculate inertia
woIdx = (j) - mod(j - 1, 4); % Corresponding wind-off index
[ResData(i, j).(type).inertiaF, ...
ResData(i, j).(type).inertiaM] = calcinertia(ResData(i, woIdx), type);
ResData(i, j).(notType).inertiaF = zeros(size(ResData(i, j).(type).inertiaF));
ResData(i, j).(notType).inertiaM = zeros(size(ResData(i, j).(type).inertiaM));
% Average everything over a mean period for the active wing
[avSignal, peakIdx] = averageperiods(ResData(i, j).(type).angles, ...
SAMPLING, ...
ResData(i, j).(type).trueFreq);
ResData(i, j).(type).avAngles = avSignal;
[ResData(i, j).(type).avFz, ResData(i, j).(type).stdFz] = getavsignal(ResData(i, j).(type).forces(:, 3), peakIdx); % mh:ignore_style (WONTFIX)
[ResData(i, j).(type).avFx, ResData(i, j).(type).stdFx] = getavsignal(ResData(i, j).(type).forces(:, 1), peakIdx); % mh:ignore_style (WONTFIX)
[ResData(i, j).(notType).avFz, ResData(i, j).(notType).stdFz] = getavsignal(ResData(i, j).(notType).forces(:, 3), peakIdx); % mh:ignore_style (WONTFIX)
[ResData(i, j).(notType).avFx, ResData(i, j).(notType).stdFx] = getavsignal(ResData(i, j).(notType).forces(:, 1), peakIdx); % mh:ignore_style (WONTFIX)
% Remove inertia and invert FX so it is oriented alongside drag diraction
ResData(i, j).(type).avFz = ResData(i, j).(type).avFz - ...
ResData(i, j).(type).inertiaF(3);
ResData(i, j).(type).avFx = -(ResData(i, j).(type).avFx - ...
ResData(i, j).(type).inertiaF(1));
% Calculate coefficient
for iPos = {'Aft', 'Front'}
pos = string(iPos);
ResData(i, j).(pos).cFz = forcetocoeff(ResData(i, j).(pos).avFz, ...
dens, speed, CHORD, SPAN, 'force');
ResData(i, j).(pos).cFx = forcetocoeff(ResData(i, j).(pos).avFx, ...
dens, speed, CHORD, SPAN, 'force');
ResData(i, j).(pos).stdFz = forcetocoeff(ResData(i, j).(pos).stdFz, ...
dens, speed, CHORD, SPAN, 'force');
ResData(i, j).(pos).stdFx = forcetocoeff(ResData(i, j).(pos).stdFx, ...
dens, speed, CHORD, SPAN, 'force');
% Calculate mean CL and mean CD over the average period
ResData(i, j).(pos).cFz_mean = mean(ResData(i, j).(pos).cFz);
ResData(i, j).(pos).cFx_mean = mean(ResData(i, j).(pos).cFx);
% Get mean STD over the period
ResData(i, j).(pos).cFz_std = mean(ResData(i, j).(pos).stdFz);
ResData(i, j).(pos).cFx_std = mean(ResData(i, j).(pos).stdFx);
end
% -----------------------------------------------
% Plot each test case
if ALLPLOTS
redFreq = redfreq(ResData(i, j).(type).trueFreq, ...
CHORD, ResData(i, j).Testcase.airspeed);
expParam = sprintf(['Aft angle = %0.1f - d = %0.2f, f = %0.2f, '...
'V = %0.1f (k = %0.02f)'], ...
ResData(i, j).(notType).angles(1), ...
ResData(i, j).Testcase.dx, ...
ResData(i, j).(type).trueFreq, ...
ResData(i, j).Testcase.airspeed, ...
redFreq);
[~, donwStrokeEndIdx] = min(ResData(i, j).(type).avAngles);
nPeriodIdx = 1 / ResData(i, j).(type).trueFreq * SAMPLING;
time = (0:length(ResData(i, j).(type).avAngles) - 1) / nPeriodIdx;
patchX = [0, donwStrokeEndIdx / nPeriodIdx, donwStrokeEndIdx / nPeriodIdx, 0];
patchY = [-5, -5, 10, 10];
figure('Name', 'HalfFlap');
ax1 = subplot(211);
setcolormap();
hold on;
patch(patchX, patchY, [186, 216, 221] / 255, 'EdgeColor', 'none', 'FaceAlpha', 0.5);
h1 = plot(time, ResData(i, j).Front.avFz);
h2 = plot(time, ResData(i, j).Front.avFx);
hold off;
setgca('XTickLabel', [], ...
'XLabel', []);
legend([h1, h2], {'\fz', '\fx'}, 'Location', 'NorthEast');
legend('boxoff');
% ax1.Position(3) = 1.25 * ax1.Position(3);
ax2 = subplot(212);
setcolormap();
hold on;
patch(patchX, patchY, [186, 216, 221] / 255, 'EdgeColor', 'none', 'FaceAlpha', 0.5);
h1 = plot(time, ResData(i, j).Aft.avFz);
h2 = plot(time, ResData(i, j).Aft.avFx);
hold off;
setgca();
linkaxes([ax1 ax2], 'xy');
ax2.Position(3) = ax1.Position(3);
% Increase axes Y lim by 10% of the data range before writing text
FACTOR = 0.1;
yDiff = diff(ax1.YLim);
ax1.YLim = [ax1.YLim(1), ax1.YLim(2) + FACTOR * yDiff];
addtxt(ax1, '\bf Front', ax1.YLim(2));
addtxt(ax2, '\bf Aft', ax2.YLim(2));
text(ax2, (donwStrokeEndIdx / nPeriodIdx) / 2, 0.5, ...
'Downstroke', ...
'HorizontalAlignment', 'center');
text(ax2, donwStrokeEndIdx / nPeriodIdx + ...
(1 - (donwStrokeEndIdx / nPeriodIdx)) / 2, 0.5, ...
'Upstroke', ...
'HorizontalAlignment', 'center');
%
% if isinteresting(ResData(i, j), SAVE_TIKZ_PARAM)
% pause(1);
% figdir = 'figures/results/';
% filename = sprintf('flap%s-Dx%0.2f_F%0.2f_V%0.1f.tex', ...
% type, ...
% ResData(i, j).Testcase.dx, ...
% ResData(i, j).Testcase.freq, ...
% ResData(i, j).Testcase.airspeed);
% save2tikz([figdir, filename], '\small');
% end
% Update titles after having saved
title(ax1, ['Front - ', expParam]);
title(ax2, ['Aft - ', expParam]);
end
end
end
% Loop on all cases and create useful vectors
nSpeeds = 4; % Number of airspeeds tested
for iDx = 1:size(ResData, 1)
for j = 2:nSpeeds
speedIdx = j:4:size(ResData, 2);
for k = 1:length(speedIdx)
speeds(j, k) = ResData(iDx, speedIdx(k)).Testcase.airspeed;
freq(j, k) = ResData(iDx, speedIdx(k)).Testcase.freq;
dx(j, k) = ResData(iDx, speedIdx(k)).Testcase.dx;
ang2(j, k) = mean(ResData(iDx, speedIdx(k)).Aft.angles);
cfzF(j, k) = ResData(iDx, speedIdx(k)).Front.cFz_mean;
cfxF(j, k) = ResData(iDx, speedIdx(k)).Front.cFx_mean;
cfzA(j, k) = ResData(iDx, speedIdx(k)).Aft.cFz_mean;
cfxA(j, k) = ResData(iDx, speedIdx(k)).Aft.cFx_mean;
stdcfzF(j, k) = ResData(iDx, speedIdx(k)).Front.cFz_std;
stdcfxF(j, k) = ResData(iDx, speedIdx(k)).Front.cFx_std;
stdcfzA(j, k) = ResData(iDx, speedIdx(k)).Aft.cFz_std;
stdcfxA(j, k) = ResData(iDx, speedIdx(k)).Aft.cFx_std;
end
figure('Name', 'Dx');
ax1 = subplot(221);
setcolormap();
hold on;
e11 = errorbar(ang2(j, 1:3), cfzF(j, 1:3), ...
stdcfzF(j, 1:3), '-s', 'Capsize', ERR_CAPSIZE);
e12 = errorbar(ang2(j, 1:3), cfxF(j, 1:3), ...
stdcfxF(j, 1:3), '-o', 'Capsize', ERR_CAPSIZE);
e11.MarkerFaceColor = e11.Color;
e12.MarkerFaceColor = e12.Color;
hold off;
setgca2('XTickLabel', [], ...
'XLabel', []);
legend({'\cl', '\cd'}, 'Location', 'SouthWest');
legend('boxoff');
ax2 = subplot(222);
setcolormap();
hold on;
e21 = errorbar(ang2(j, 4:end), cfzF(j, 4:end), ...
stdcfzF(j, 4:end), '-s', 'Capsize', ERR_CAPSIZE);
e22 = errorbar(ang2(j, 4:end), cfxF(j, 4:end), ...
stdcfxF(j, 4:end), '-o', 'Capsize', ERR_CAPSIZE);
e21.MarkerFaceColor = e21.Color;
e22.MarkerFaceColor = e22.Color;
hold off;
setgca2('XTickLabel', [], ...
'XLabel', [], ...
'YTickLabel', [], ...
'YLabel', []);
ax3 = subplot(223);
setcolormap();
hold on;
cosd(ang2(j, 4:end));
e31 = errorbar(ang2(j, 1:3), cfzA(j, 1:3) ./ cosd(ang2(j, 4:end)), ...
stdcfzA(j, 1:3), '-s', 'Capsize', ERR_CAPSIZE);
e32 = errorbar(ang2(j, 1:3), cfxA(j, 1:3) ./ cosd(ang2(j, 4:end)), ...
stdcfxA(j, 1:3), '-o', 'Capsize', ERR_CAPSIZE);
e31.MarkerFaceColor = e31.Color;
e32.MarkerFaceColor = e32.Color;
hold off;
setgca2();
ylabel('$\cl^*$ and $\cd^*$ [-]');
ax4 = subplot(224);
setcolormap();
hold on;
e41 = errorbar(ang2(j, 4:end), cfzA(j, 4:end) ./ cosd(ang2(j, 4:end)), ...
stdcfzA(j, 4:end), '-s', 'Capsize', ERR_CAPSIZE);
e42 = errorbar(ang2(j, 4:end), cfxA(j, 4:end) ./ cosd(ang2(j, 4:end)), ...
stdcfxA(j, 4:end), '-o', 'Capsize', ERR_CAPSIZE);
e41.MarkerFaceColor = e41.Color;
e42.MarkerFaceColor = e42.Color;
hold off;
setgca2('YTickLabel', [], ...
'YLabel', []);
linkaxes([ax1 ax2 ax3 ax4], 'xy');
% Add annotations
% Increase axes Y lim by 10% of the data range before writing text
FACTOR = 0.1;
yDiff = diff(ax1.YLim);
ax1.YLim = [ax1.YLim(1), ax1.YLim(2) + FACTOR * yDiff];
addtxt(ax1, '$\mathbf{\freq}$ = 1.25 Hz (Front)', ax1.YLim(2));
addtxt(ax2, '$\mathbf{\freq}$ = 2.00 Hz (Front)', ax2.YLim(2));
addtxt(ax3, '$\mathbf{\freq}$ = 1.25Hz (Aft)', ax3.YLim(2));
addtxt(ax4, '$\mathbf{\freq}$ = 2.00 Hz (Aft)', ax4.YLim(2));
pause(1);
figdir = 'figures/results/';
filename = sprintf('half%s-AllF-Dx%0.2f_V%0.1f.tex', ...
type, ...
dx(j, 1), ...
speeds(j, 1));
save2tikz([figdir, filename], '\small');
expParam = sprintf('Dx = %0.02f, U = %0.2f', ...
dx(j, 1), ...
speeds(j, 1));
title(ax1, expParam);
title(ax3, expParam);
end
end
end
function addtxt(ax, txt, ypos)
text(ax, -10, ypos, ...
txt, ...
'HorizontalAlignment', 'left', 'VerticalAlignment', 'top', 'FontWeight', 'bold');
end
function [inertiaF, inertiaM] = calcinertia(ResDataWO, type)
% CALCINERTIA Calcualte inertia forces
SAMPLING = 1000;
% Get first and last peaks for wind-off conditions
woBounds = getboundingpeaks(ResDataWO.(type).angles, SAMPLING);
woIdx = woBounds(1):woBounds(2);
% Calculate mean force and moments due to inertia
inertiaF = mean(ResDataWO.(type).forces(woIdx, :));
inertiaM = mean(ResDataWO.(type).moments(woIdx, :));
end
function [avSignal, peakIdx] = averageperiods(signal, sampling, freq)
% AVERAGEPERIOD Average all periods of the signal and return the average signal
% Find all peaks location
period = 1 / freq;
nPeriodIdx = period * sampling;
peakLocs = getallpeaks(signal, sampling);
% Remove first and last peaks
peakLocs = peakLocs(2:end - 1);
% Split signal in a matrix whith rows for the peak number and cols to the INDEXES of values in
for iPeak = length(peakLocs):-1:1
peakIdx(iPeak, :) = peakLocs(iPeak):peakLocs(iPeak) + round(nPeriodIdx);
peakSignal(iPeak, :) = signal(peakIdx(iPeak, :));
end
% Take the mean value of the signal formed with all these peaks
avSignal = mean(peakSignal);
end
function [avSignal, stdSignal] = getavsignal(signal, peakIdx)
for iPeak = size(peakIdx, 1):-1:1
peakSignal(iPeak, :) = signal(peakIdx(iPeak, :));
end
% Take the mean value of the signal formed with all these peaks
avSignal = mean(peakSignal);
stdSignal = std(peakSignal);
end
function setgca(varargin)
ylim([-1.5, 1.5]);
xlim([0, 1]);
xlabel('t/T [-]');
ylabel('\fz and \fx [N]');
set(gca, ...
'Box', 'off', ...
'TickDir', 'out', ...
'TickLength', [.02 .02], ...
'XMinorTick', 'off', ...
'YMinorTick', 'off', ...
'YGrid', 'off', ...
'XGrid', 'off', ...
'XColor', 'k', ...
'YColor', 'k', ...
'GridLineStyle', ':', ...
'GridColor', 'k', ...
'GridAlpha', 0.25, ...
'LineWidth', 1, ...
'FontName', 'Helvetica', ...
'Fontsize', 14);
if nargin > 0
set(gca, varargin{:});
end
end
function setgca2(varargin)
% ylim([-1.5, 1.5])
xlim([-13, 40]);
xticks([-10:10:40]);
%
xlabel('Aft wing dihedral [deg]');
ylabel('\cl and \cd [-]');
set(gca, ...
'Box', 'off', ...
'TickDir', 'out', ...
'TickLength', [.02 .02], ...
'XMinorTick', 'off', ...
'YMinorTick', 'off', ...
'YGrid', 'off', ...
'XGrid', 'off', ...
'XColor', 'k', ...
'YColor', 'k', ...
'GridLineStyle', ':', ...
'GridColor', 'k', ...
'GridAlpha', 0.25, ...
'LineWidth', 1, ...
'FontName', 'Helvetica', ...
'Fontsize', 14);
if nargin > 0
set(gca, varargin{:});
end
end
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