From 55dff5cacede17b4f11e8272622e7687b7b09733 Mon Sep 17 00:00:00 2001
From: Thomas Lambert <t.lambert@uliege.be>
Date: Mon, 12 Dec 2022 15:00:40 +0100
Subject: [PATCH] feat(plots): add static and semi flap plots
---
utils/analysis/plotstatictests.m | 128 ++++++++++
utils/plotsemiflap.m | 418 +++++++++++++++++++++++++++++++
2 files changed, 546 insertions(+)
create mode 100644 utils/analysis/plotstatictests.m
create mode 100644 utils/plotsemiflap.m
diff --git a/utils/analysis/plotstatictests.m b/utils/analysis/plotstatictests.m
new file mode 100644
index 0000000..12c5142
--- /dev/null
+++ b/utils/analysis/plotstatictests.m
@@ -0,0 +1,128 @@
+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
diff --git a/utils/plotsemiflap.m b/utils/plotsemiflap.m
new file mode 100644
index 0000000..499862d
--- /dev/null
+++ b/utils/plotsemiflap.m
@@ -0,0 +1,418 @@
+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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