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resultplot.m
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function []=resultplot(var)
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% Copyright (C) 1999, 2007 Tomas Melin
%
% This file is part of Tornado
%
% Tornado is free software; you can redistribute it and/or
% modify it under the terms of the GNU General Public
% License as published by the Free Software Foundation;
% either version 2, or (at your option) any later version.
%
% Tornado is distributed in the hope that it will be useful,
% but WITHOUT ANY WARRANTY; without even the implied
% warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR
% PURPOSE. See the GNU General Public License for more
% details.
%
% You should have received a copy of the GNU General Public
% License along with Tornado; see the file GNU GENERAL
% PUBLIC LICENSE.TXT. If not, write to the Free Software
% Foundation, 59 Temple Place -Suite 330, Boston, MA
% 02111-1307, USA.
%
%%% Result plot function
%
% This function plots the results of a tornado run using standard Matlab
% plots. The function reads the output files and displays the data.
%
% usage: []=resultplot(VAR)
%
% VAR is the selector for which type of results should be plotted. The
% selector is choosen in postproc, and the list of choises are listed in
% questions(8).
%
%
% Author: Tomas Melin <melin@kth.se>
% Keywords: Tornado interface function.
%
% Revision History:
% Bristol, 2007 06 27: Addition of new header. TM.
% Spånga, 2021-09-19: Updated to MATLAB R2020, TM
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
settings=config('startup');
%disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
%disp('Available static solution result files are: ')
%cd(settings.odir)%
% dir *-Cx.mat
%cd(settings.hdir)
%data=questions(10);
%if isempty(data)
% data=('trial');
%end
switch var
case 1
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available static solution result files are: ')
ls([settings.odir,'/','*-Cx.mat'])
data=questions(10);
fname=strcat(data,'-Cx');
load([settings.odir,'/', fname]);
[x, y, z]=midpoint(lattice.XYZ);
d=size(z,2);
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
figure(4)% Delta cp plot
rotate3d on
colormap(hot);
fill3(lattice.XYZ(:,:,1)',lattice.XYZ(:,:,2)',lattice.XYZ(:,:,3)',results.cp')
title('Delta cp distribution')
colorbar('vert')
axis equal
%*************************************************
% Spanload plot, first attempt.
try
figure(10)
hold on, grid on
plot(results.ystation(:,1),results.ForcePerMeter(:,1));
title('Spanload on main wing');
ylabel('Force per meter');
xlabel('Spanstation')
catch
end
%Local CL plot
try
figure(11)
hold on, grid on
plot(results.ystation(:,1),results.CL_local(:,1));
title('Local CL on main wing');
ylabel('CL');
xlabel('Spanstation')
text(0,0,strcat('Total CL ',num2str(results.CL)));
figure(12)
hold on, grid on
plot(results.ystation(:,1),results.CD_local(:,1));
title('Local CD on main wing');
ylabel('CD');
xlabel('Spanstation')
text(0,0,strcat('Total CD ',num2str(results.CD)));
catch
end
try
figure(13)
hold on, grid on
plot(results.ystation(:,1)./(ref.b_ref/2),results.CL_local(:,1)./results.CL);
title('Normalized Local CL on main wing');
ylabel('Normalized CL');
xlabel('Normalized spanstation, \eta, [-]')
catch
end
try
%% Bending moment diagram
%Bending moment computation disabeled in version 136, moved to
%structural comoutation.
figure(14)
hold on, grid on
title('Bending moment on main wing');
ylabel('Bending moment, M_b, [Nm]');
xlabel('Spanstation, y, [m]')
plot(results.ystation(:,1),results.bend(:,1))
figure(15)
plot(results.ystation(:,1),results.shear(:,1)) ;
hold on, grid on
title('Shear force on main wing');
ylabel('Shear force, F_s, [N]');
xlabel('Spanstation, y, [m]')
catch
end
%*************************************************
figure(7)
axis off
set(gcf, 'Position', [100, 100, 560, 800])
text(-0.10,1.05,'Tornado Computation Results, version 136 ')
%%
%% Run block
sy=.925;
sx=-0.1;
text(sx,sy+0.075,'JID: '); text(sx+0.25,sy+0.075,data)
text(sx,sy+0.05,'Run end time: '); text(sx+0.25,sy+0.05,results.rundate)
text(sx,sy+0.025,'Geometry: '); if isempty(geo.name); geo.name='N/A'; end; text(sx+0.25,sy+0.025,geo.name)
text(sx,sy,'Project: '); if isempty(geo.project); geo.project='N/A'; end; text(sx+0.25,sy,geo.project)
text(sx+0.6,sy,'Downwash matrix condition: '); text(sx+1,sy,num2str(results.dwcond))
%% reference block
sy=.825;
sx=-0.1;
text(sx,sy+0.05,'Reference area: '); text(sx+0.25,sy+0.05,num2str(ref.S_ref));
text(sx,sy+0.025,'Reference chord: '); text(sx+0.25,sy+0.025,num2str(ref.C_mac));
text(sx,sy,'Reference span: '); text(sx+0.25,sy,num2str(ref.b_ref));
text(sx+0.4,sy+0.05,'Reference'); text(sx+0.6,sy+0.05,num2str(geo.ref_point(1)));
text(sx+0.4,sy+0.025,'point pos: '); text(sx+0.6,sy+0.025,num2str(geo.ref_point(2)));
text(sx+0.6,sy,num2str(geo.ref_point(3)));
text(sx+0.75,sy+0.025,'Center of gravity: ');text(sx+1.05,sy+0.05,num2str(geo.CG(1)));
text(sx+1.05,sy+0.025,num2str(geo.CG(2)));
text(sx+1.05,sy,num2str(geo.CG(3)));
annotation('rectangle',[0.03 0.765 .94 .07],'Color','black')
% State block
sy=0.7;
sx=-0.1;
text(sx,sy+0.075,'STATE: ');
text(sx,sy+0.05,'\alpha [deg]: '); text(sx+.25,sy+0.05,num2str(state.alpha*180/pi));
text(sx,sy+0.025,'\beta [deg]: '); text(sx+.25,sy+0.025,num2str(state.betha*180/pi));
text(sx,sy,'\alpha_{dot} [rad/s]: '); text(sx+.25,sy,num2str(state.alphadot));
text(sx,sy-0.025,'\beta_{dot} [rad/s]: '); text(sx+.25,sy-0.025,num2str(state.bethadot));
text(sx+0.8,sy+0.05,'P [rad/s]: '); text(sx+.95,sy+0.05,num2str(state.P));
text(sx+0.8,sy+0.025,'Q [rad/s]: '); text(sx+.95,sy+0.025,num2str(state.Q));
text(sx+0.8,sy,'R [rad/s]: '); text(sx+.95,sy,num2str(state.R));
text(sx+0.8,sy-0.025,'PG Corr.: '); text(sx+0.95,sy-0.025,num2str(state.pgcorr))
[void sos void]=ISAtmosphere(state.ALT);
Mach=state.AS/sos;
text(sx+0.4,sy+0.05,'Airspeed: '); text(sx+0.6,sy+0.05,num2str(state.AS));
text(sx+0.4,sy+0.025,'Altitude: '); text(sx+0.6,sy+0.025,num2str(state.ALT));
text(sx+0.4,sy,'Density: '); text(sx+0.6,sy,num2str(state.rho));
text(sx+0.4,sy-0.025,'Mach: '); text(sx+0.6,sy-0.025,num2str(Mach));
FV=geo.flap_vector(find(geo.flapped==1));
text(sx,.1,'Rudder setting [deg]:'); text(sx+0.4,.1,num2str(FV*180/pi));
VV=geo.allmove_def(find(geo.allmove==1));
text(sx+0.5,.1,'Allmoving wing setting [deg]:'); text(sx+1,.1,num2str(VV*180/pi));
% Forces block
sy=0.55;
sx=-0.1;
text(sx,sy+0.075,'Net Wind Forces: (N)');
text(sx,sy+0.05,'Drag: '); text(sx+0.1,sy+0.05,num2str(results.D));
text(sx,sy+0.025,'Side: '); text(sx+0.1,sy+0.025,num2str(results.C));
text(sx,sy,'Lift: '); text(sx+0.1,sy,num2str(results.L));
text(sx+0.4,sy+0.075,'Net Body Forces: (N)');
text(sx+0.4,sy+0.05,'X: '); text(sx+0.5,sy+0.05,num2str(results.FORCE(1)));
text(sx+0.4,sy+0.025,'Y: '); text(sx+0.5,sy+0.025,num2str(results.FORCE(2)));
text(sx+0.4,sy,'Z: '); text(sx+0.5,sy,num2str(results.FORCE(3)));
text(0.7,sy+0.075,'Net Body Moments: (Nm)');
text(sx+0.8,sy+0.05,'Roll: '); text(sx+0.9,sy+0.05,num2str(r4dec(results.MOMENTS(1))));
text(sx+0.8,sy+0.025,'Pitch: '); text(sx+0.9,sy+0.025,num2str(r4dec(results.MOMENTS(2))));
text(sx+0.8,sy,'Yaw: '); text(sx+0.9,sy,num2str(r4dec(results.MOMENTS(3))));
% Coeff block
sy=0.45;
sx=-0.1;
text(sx,sy+0.05,'CL '); text(sx+0.2,sy+0.05,num2str(r4dec(results.CL)));
text(sx,sy+0.025, 'CD '); text(sx+0.2,sy+0.025,num2str(r4dec(results.CD))) ;
text(sx,sy,'CY '); text(sx+0.2,sy,num2str(r4dec(results.CY)));
text(sx,sy-0.025,'CD_t_r_e_f_f_t_z ');
try
text(sx+0.2,sy-0.025,num2str(results.Trefftz_drag_Coeff))
catch
text(sx+0.2,sy-0.025,'N/A')
end
text(sx+0.4,sy+0.05,'CZ '); text(sx+0.55,sy+0.05,num2str(r4dec(results.CZ)));
text(sx+0.4,sy+0.025,'CX '); text(sx+0.55,sy+0.025,num2str(r4dec(results.CX)));
text(sx+0.4,sy,'CC '); text(sx+0.55,sy,num2str(r4dec(results.CC)));
text(sx+0.8,sy+0.05,'Cm '); text(sx+0.9,sy+0.05,num2str(r4dec(results.Cm)));
text(sx+0.8,sy+0.025,'Cn '); text(sx+0.9,sy+0.025,num2str(r4dec(results.Cn)));
text(sx+0.8,sy,'Cl '); text(sx+0.9,sy,num2str(r4dec(results.Cl)));
%% Per Wing Block
sy=0.25;
sx=-0.1;
text(sx,sy+0.05,'CL per wing '); text(sx+0.2,sy+0.05,num2str(r4dec(results.CLwing')));
text(sx+0.4,sy+0.05,'CD per wing '); text(sx+0.65,sy+0.05,num2str(r4dec(results.CDwing')));
text(sx+0.8,sy+0.05,'CY per wing '); text(sx+1.05,sy+0.05,num2str(r4dec(results.CYwing')));
%%%%%
%
%%%%%
figure(8)
axis off
grid on
text(0,1,'TORNADO CALCULATION RESULTS, Derivatives')
text(0,.95,'JID: '); text(0.25,0.95,data)
text(0,.90,'Reference area: '); text(0.25,0.90,num2str( ref.S_ref ));
text(0,.85,'Reference chord: '); text(0.25,.85,num2str(ref.C_mac));
text(0,.8,'Reference span: '); text(0.25,.8,num2str(ref.b_ref));
text(0.4,.90,'\alpha [deg]: '); text(.55,.9,num2str(state.alpha*180/pi));
text(0.4,.85, '\beta [deg]: '); text(.55,.85,num2str(state.betha*180/pi));
text(0.4,.8,'Airspeed: '); text(.55,.8,num2str(r2dec(state.AS)));
text(0.65,.9, 'P [rad/s]: '); text(.8,.9,num2str(state.P));
text(0.65,.85,'Q[rad/s]: '); text(.8,.85,num2str(state.Q));
text(0.65,.8,' R[rad/s]: '); text(.8,.8,num2str(state.R));
figure(8)
text(0,.7,'CL derivatives : ');
text(0,.65,'CL_{\alpha}'); text(0.15,.65,num2str(r4dec(results.CL_a)));
text(0,.6,'CL_{\beta}'); text(0.15,.6,num2str(r4dec(results.CL_b)));
text(0,.55,'CL_P'); text(0.15,.55,num2str(r4dec(results.CL_P)));
text(0,.5,'CL_Q'); text(0.15,.5,num2str(r4dec(results.CL_Q)));
text(0,.45,'CL_R'); text(0.15,.45,num2str(r4dec(results.CL_R)));
text(0,.35,'Roll derivatives : ');
text(0,.3,'Cl_{\alpha}'); text(0.15,.3,num2str(r4dec(results.Cl_a)));
text(0,.25,'Cl_{\beta}'); text(0.15,.25,num2str(r4dec(results.Cl_b)));
text(0,.2,'Cl_P'); text(0.15,.2,num2str(r4dec(results.Cl_P)));
text(0,.15,'Cl_Q'); text(0.15,.15,num2str(r4dec(results.Cl_Q)));
text(0,.1,'Cl_R'); text(0.15,.1,num2str(r4dec(results.Cl_R)));
text(0.35,.7,'CD derivatives : ');
text(0.35,.65,'CD_{\alpha}'); text(0.5,.65,num2str(r4dec(results.CD_a)));
text(0.35,.6,'CD_{\beta}'); text(0.5,.6,num2str(r4dec(results.CD_b)));
text(0.35,.55,'CD_P'); text(0.5,.55,num2str(r4dec(results.CD_P)));
text(0.35,.5,'CD_Q'); text(0.5,.5,num2str(r4dec(results.CD_Q)));
text(0.35,.45,'CD_R'); text(0.5,.45,num2str(r4dec(results.CD_R)));
text(0.35,.35,'Pitch derivatives : ');
text(0.35,.3,'Cm_{\alpha}'); text(.5,.3,num2str(r4dec(results.Cm_a)));
text(0.35,.25,'Cm_{\beta}'); text(0.5,.25,num2str(r4dec(results.Cm_b)));
text(0.35,.2,'Cm_P'); text(0.5,.2,num2str(r4dec(results.Cm_P)));
text(0.35,.15,'Cm_Q'); text(0.5,.15,num2str(r4dec(results.Cm_Q)));
text(0.35,.1,'Cm_R'); text(0.5,.1,num2str(r4dec(results.Cm_R)));
text(0.7,.7,'CY derivatives : ');
text(0.7,.65,'CY_{\alpha}'); text(0.85,.65,num2str(r4dec(results.CY_a)));
text(0.7,.6,'CY_{\beta}'); text(0.85,.6,num2str(r4dec(results.CY_b)));
text(0.7,.55,'CY_P'); text(0.85,.55,num2str(r4dec(results.CY_P)));
text(0.7,.5,'CY_Q'); text(0.85,.5,num2str(r4dec(results.CY_Q)));
text(0.7,.45,'CY_R'); text(0.85,.45,num2str(r4dec(results.CY_R)));
text(0.7,.35,'Yaw derivatives : ');
text(0.7,.3,'Cn_{\alpha}'); text(.85,.3,num2str(r4dec(results.Cn_a)));
text(0.7,.25,'Cn_{\beta}'); text(0.85,.25,num2str(r4dec(results.Cn_b)));
text(0.7,.2,'Cn_P'); text(0.85,.2,num2str(r4dec(results.Cn_P)));
text(0.7,.15,'Cn_Q'); text(0.85,.15,num2str(r4dec(results.Cn_Q)));
text(0.7,.1,'Cn_R'); text(0.85,.1,num2str(r4dec(results.Cn_R)));
figure(9)
axis off
%grid on
text(0,1,'TORNADO CALCULATION RESULTS, Central difference, RUDDER DERIVs')
text(0,.95,'JID: '); text(0.25,0.95,data)
text(0,.90,'Reference area: '); text(0.25,0.90,num2str(ref.S_ref));
text(0,.85,'Reference chord: ');text(0.25,.85,num2str(ref.C_mac));
text(0,.8,'Reference span: ');text(0.25,.8,num2str(ref.b_ref));
text(0.4,.90,'\alpha: '); text(.55,.9,num2str(state.alpha*180/pi));
text(0.4,.85,'\beta: '); text(.55,.85,num2str(state.betha*180/pi));
text(0.4,.8,'Airspeed: '); text(.55,.8,num2str(r2dec(state.AS)));
text(0.65,.9,'P: '); text(.8,.9,num2str(state.P));
text(0.65,.85,'Q: '); text(.8,.85,num2str(state.Q));
text(0.65,.8,'R: '); text(.8,.8,num2str(state.R));
text(0,.45,'CL_{\delta}'); text(0.15,.45,num2str(results.CL_d'));
text(0,.05,'Cl_{\delta}'); text(0.15,.05,num2str(results.Cl_d'));
text(0.35,.45,'CD_{\delta}'); text(0.5,.45,num2str(results.CD_d'));
text(0.35,.05,'Cm_{\delta}'); text(0.5,.05,num2str(results.Cm_d'));
text(0.7,.45,'CY_{\delta}'); text(0.85,.45,num2str(results.CY_d'));
text(0.7,.05,'Cn_{\delta}'); text(0.85,.05,num2str(results.Cn_d'));
try
%Bend and shear plot
%%%%%%%%%%%%%%%%5
%Stuff below is experimental
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
%Hardcoded to plot the first wing data.
H=figure(1);
hold on
set(H,'Position',[10 10 0.8*3*210 0.8*3*297])
%Changing variables to plot only partition outline
g2=geo;
g2.nwing=1;
g2.nx=double(g2.nx>0);
g2.ny=double(g2.ny>0);
g2.fnx=double(g2.fnx>0);
g2.symetric=geo.symetric(1);
g2.nx=g2.nx(1,:);
g2.ny=g2.ny(1,:);
g2.fnx=g2.fnx(1,:);
g2.nelem=g2.nelem(1);
g2.flapped=geo.flapped(1,:);
g2.fsym=geo.fsym(1,:);
g2.flap_vector=geo.flap_vector(1,:);
s2.AS=1;
s2.alpha=0;
s2.betha=0;
s2.P=0;
s2.Q=0;
s2.R=0;
s2.ALT=0;
s2.rho=1;
s2.pgcorr=0;
[l2,ref]=fLattice_setup2(g2,s2,1);
subplot('position',[0.1 0.8 0.8 0.17]); hold on
%axes('position',[0.1 0.8 0.8 0.17])
g=fill3(l2.XYZ(:,:,1)',l2.XYZ(:,:,2)',l2.XYZ(:,:,3)','w');
set(g,'LineWidth',2);
view([90,90]);
%axis equal
hold on
%xlabel('Aircraft body x-coordinate')
%ylabel('Aircraft body y-coordinate')
%zlabel('Aircraft body z-coordinate')
title('Wing aerodynamic loading')
axis off
subplot(4,1,2)
%axes()
h1=plot(results.ystation(:,1),results.shear(:,1));
hold on
set(h1,'LineWidth',2)
h2=gca;
%set(h2,'XTickLabel',[],'position',[0.1 0.6 0.8 0.17])
grid on
ylabel('Shear force, F_z, [N]')
subplot(4,1,3)
%axes();
h1=plot(results.ystation(:,1),results.bend(:,1));
hold on
set(h1,'LineWidth',2)
h2=gca;
%set(h2,'XTickLabel',[],'position',[0.1 0.4 0.8 0.17])
grid on
ylabel('Bend moment, M_x, [Nm]')
subplot(4,1,4)
%axes('position',[0.1 0.2 0.8 0.17]);
h1=plot(results.ystation(:,1),results.twist(:,1));
hold on
set(h1,'LineWidth',2)
%h2=gca;
%set(h5,'OuterPosition',[0 0.0 1 0.2])
grid on
ylabel('Twist moment, M_y, [Nm]')
xlabel('Span station, y, [m]')
h2=gca;
%set(h2,'position',[0.1 0.2 0.8 0.17])
end
case 2
%Case removed
case 3
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available alpha sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_alpha.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_alpha');
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(15)
subplot(3,2,3), plot(results.alpha_sweep,squeeze(results.matrix(2,1,:)));
xlabel('Alpha [rad]')
ylabel('CD')
subplot(3,2,5), plot(results.alpha_sweep,squeeze(results.matrix(3,1,:)));
xlabel('Alpha [rad]')
ylabel('CY')
subplot(3,2,2), plot(results.alpha_sweep,squeeze(results.matrix(4,1,:)));
xlabel('Alpha [rad]')
ylabel('Cl')
subplot(3,2,4), plot(results.alpha_sweep,squeeze(results.matrix(5,1,:)));
xlabel('Alpha [rad]')
ylabel('Cm')
subplot(3,2,6), plot(results.alpha_sweep,squeeze(results.matrix(6,1,:)));
xlabel('Alpha [rad]')
ylabel('Cn')
subplot(3,2,1), plot(results.alpha_sweep,squeeze(results.matrix(1,1,:)));
xlabel('Alpha [rad]')
ylabel('CL')
axes
text(0.0,1.05,'Coefficient dependency on alpha');
axis off
figure(16)
plot(squeeze(results.matrix(1,1,:)),squeeze(results.matrix(2,1,:)));
xlabel('CL,[-].');
ylabel('CD,[-].');
title('Induced Drag Polar');
grid
hold on
figure(17)
alpha1=results.alpha_sweep.*180/pi;
CL=squeeze(results.matrix(1,1,:));
CD=squeeze(results.matrix(2,1,:));
Cm=squeeze(results.matrix(5,1,:));
faeropolar(alpha1,CL,CD,Cm,'-o');
try
alpha1=results.alpha_sweep.*180/pi;
delta1=results.rudderangle.*180/pi;
figure(18)
plot(alpha1,delta1)
xlabel('Angle of attack, \alpha, [deg].')
ylabel('Control effector deflection, \delta, [deg].')
title('Effector angle to trim.')
%hold on
end
case 4
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available beta sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_beta.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_beta')
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(10)
subplot(3,2,1), plot(results.betha_sweep,squeeze(results.matrix(1,1,:)));
xlabel('Beta [rad]')
ylabel('CL')
subplot(3,2,3), plot(results.betha_sweep,squeeze(results.matrix(2,1,:)));
xlabel('Beta [rad]')
ylabel('CD')
subplot(3,2,5), plot(results.betha_sweep,squeeze(results.matrix(3,1,:)));
xlabel('Beta [rad]')
ylabel('CY')
subplot(3,2,2), plot(results.betha_sweep,squeeze(results.matrix(4,1,:)));
xlabel('Beta [rad]')
ylabel('Cl')
subplot(3,2,4), plot(results.betha_sweep,squeeze(results.matrix(5,1,:)));
xlabel('Beta [rad]')
ylabel('Cm')
subplot(3,2,6), plot(results.betha_sweep,squeeze(results.matrix(6,1,:)));
xlabel('Beta [rad]')
ylabel('Cn')
axes
text(0.0,1.05,'Coefficient dependency on beta (sideslip)')
axis off
case 5
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available rudder sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_d.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_d')
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(11)
subplot(3,2,1), plot(results.delta_sweep,squeeze(results.matrix(1,1,:)));
xlabel('Delta [rad]')
ylabel('CL')
subplot(3,2,3), plot(results.delta_sweep,squeeze(results.matrix(2,1,:)));
xlabel('Delta [rad]')
ylabel('CD')
subplot(3,2,5), plot(results.delta_sweep,squeeze(results.matrix(3,1,:)));
xlabel('Delta [rad]')
ylabel('CY')
subplot(3,2,2), plot(results.delta_sweep,squeeze(results.matrix(4,1,:)));
xlabel('Delta [rad]')
ylabel('Cl')
subplot(3,2,4), plot(results.delta_sweep,squeeze(results.matrix(5,1,:)));
xlabel('Delta [rad]')
ylabel('Cm')
subplot(3,2,6), plot(results.delta_sweep,squeeze(results.matrix(6,1,:)));
xlabel('Delta [rad]')
ylabel('Cn')
axes
text(0.0,1.05,'Coefficient dependency on delta (rudder deflection)')
axis off
case 6
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available roll speed sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_P.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_P')
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(12)
subplot(3,2,1), plot(results.P_sweep,squeeze(results.matrix(1,1,:)));
xlabel('P [-]')
ylabel('CL [-]')
subplot(3,2,3), plot(results.P_sweep,squeeze(results.matrix(2,1,:)));
xlabel('P [-]')
ylabel('CD [-]')
subplot(3,2,5), plot(results.P_sweep,squeeze(results.matrix(3,1,:)));
xlabel('P [-]')
ylabel('CY [-]')
subplot(3,2,2), plot(results.P_sweep,squeeze(results.matrix(4,1,:)));
xlabel('P [-]')
ylabel('Cl [-]')
subplot(3,2,4), plot(results.P_sweep,squeeze(results.matrix(5,1,:)))
xlabel('P [-]')
ylabel('Cm [-]')
subplot(3,2,6), plot(results.P_sweep,squeeze(results.matrix(6,1,:)));
xlabel('P [-]')
ylabel('Cn [-]')
axes
text(0.0,1.05,'Coefficient dependency on P (Roll speed)')
axis off
case 7
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available pitch speed sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_Q.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_Q')
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(14)
subplot(3,2,1), plot(results.Q_sweep,squeeze(results.matrix(1,1,:)));
xlabel('Q [-]')
ylabel('CL [-]')
subplot(3,2,3), plot(results.Q_sweep,squeeze(results.matrix(2,1,:)));
xlabel('Q [-]')
ylabel('CD [-]')
subplot(3,2,5), plot(results.Q_sweep,squeeze(results.matrix(3,1,:)));
xlabel('Q [-]')
ylabel('CY [-]')
subplot(3,2,2), plot(results.Q_sweep,squeeze(results.matrix(4,1,:)));
xlabel('Q [-]')
ylabel('Cl [-]')
subplot(3,2,4), plot(results.Q_sweep,squeeze(results.matrix(5,1,:)));
xlabel('Q [-]')
ylabel('Cm [-]')
subplot(3,2,6), plot(results.Q_sweep,squeeze(results.matrix(6,1,:)));
xlabel('Q [-]')
ylabel('Cn [-]')
axes
text(0.0,1.05,'Coefficient dependency on Q (Pitch speed)')
axis off
case 8
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available yaw speed sweep solution result files are: ')
ls([settings.odir,'/','*-Cx_R.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx_R')
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(13)
subplot(3,2,1), plot(results.R_sweep,squeeze(results.matrix(1,1,:)));
xlabel('R [-]')
ylabel('CL [-]')
subplot(3,2,3), plot(results.R_sweep,squeeze(results.matrix(2,1,:)));
xlabel('R [-]')
ylabel('CD [-]')
subplot(3,2,5), plot(results.R_sweep,squeeze(results.matrix(3,1,:)));
xlabel('R [-]')
ylabel('CY [-]')
subplot(3,2,2), plot(results.R_sweep,squeeze(results.matrix(4,1,:)));
xlabel('R [-]')
ylabel('Cl [-]')
subplot(3,2,4), plot(results.R_sweep,squeeze(results.matrix(5,1,:)));
xlabel('R [-]')
ylabel('Cm [-]')
subplot(3,2,6), plot(results.R_sweep,squeeze(results.matrix(6,1,:)));
xlabel('R [-]')
ylabel('Cn [-]')
axes
text(0.0,1.05,'Coefficient dependency on R (Yaw speed)')
axis off
%end
case 9
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available static solution result files are: ')
ls([settings.odir,'/','*-Cx.mat'])
data=questions(10);
try
fname=strcat(data,'-Cx');
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
results=trefftz5(results,state,geo,lattice,ref);
x=results.treffts.x;
y=results.treffts.y;
D=results.treffts.D;
VTOT=results.treffts.VTOT;
VVEC=results.treffts.VVEC;
figure(23)
surf(x,y,D)
xlabel('y coordinate, [m]')
ylabel('z coordinate, [m]')
zlabel('Distributed drag contrubution, [N]')
title('Trefftz plane drag contribution field.') %*** Treffz changed to Trefftz (AT)
figure(22)
contour(x,y,VTOT,20), hold on
quiver(x,y,VVEC(:,:,1),VVEC(:,:,2),5)
xlabel('y coordinate, [m]')
ylabel('z coordinate, [m]')
title('Trefftz plane velocity vector field.') %*** Treffz changed to Trefftz (AT)
fname=strcat(data,'-Cx');
save([settings.odir,'/',fname,'results','geo','lattice','state','ref'])
case 10
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available flap plate drag result files are: ')
ls([settings.odir,'/','*-Cnull.mat'])
data=questions(10);
try
fname=strcat(data,'-Cnull');
load([settings.odir,'/', fname]);
catch
terror(12)
return
end
figure(31)
axis off
grid on
text(0,1,'TORNADO Zero lift drag estimation.')
text(0,.95,'JID: '); text(0.25,0.95,data)
text(0,.90,'Reference area: '); text(0.25,0.90,num2str( ref.S_ref ));
text(0,.85,'Reference chord: ');text(0.25,.85,num2str(ref.C_mac));
text(0,.8,'Reference span: ');text(0.25,.8,num2str(ref.b_ref));
text(0.65,.95,'Re: '); text(.8,.95,num2str(round(results.Re)));
text(0.65,.9,'CD_0: '); text(.8,.9,num2str(sum(sum(results.CD0))));
text(0.65,.85,'Swet: '); text(.8,.85,num2str(sum(sum(results.Swet))));
text(0.65,.8,'Volume: '); text(.8,.8,num2str(sum(sum(results.Vol))));
text(0.0,.60,'Zero lift drag per part: '); text(0.35,.6,num2str(results.CD0));
text(0.0,.35,'Wetted area per part: '); text(0.35,.35,num2str(results.Swet));
text(0.0,.1,'Internal volume per part: '); text(0.35,.1,num2str(results.Vol));
%text(0.0,.6,'Side: '); text(0.1,.6,num2str(results.C));
%text(0.0,.55,'Lift: '); text(0.1,.55,num2str(results.L));
case 11 %***
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available polar breakdown result files are: ')
ls([settings.odir,'/','*-Cx_drginf.mat'])
data=questions(10);
try %***
fname=strcat(data,'-Cx_drginf'); %***
%fname=strcat(data,'-Cx_drgout'); %*** alternative
load([settings.odir,'/', fname]);
catch %***
terror(12) %***
return %***
end %***
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %***
%function drgplot() %***
drgdata=zeros(numbmhs+1,numbcls+1,5); %*** contains drag components to plot in stacked columns
%*** if more drag components are to be added change '5' to required
%*** number of components and add/remove components below
for i=1:1:numbmhs+1 %***
drgdata(i,:,1)=vorinrd; %*** auto-vortex induced drag of wing
drgdata(i,:,3)=PROFCOR; %*** form drag as a function of op. CL
end %***
drgdata(:,:,2)=EZELDRG; %*** zero-lift drag
drgdata(:,:,4)=TTLTRMD; %*** total trim drag
drgdata(:,:,5)=TCDCINC; %*** compressibility drag
drgdata(1,:,:)=[]; %***
drgdata(:,1,:)=[]; %***
drgdata=permute(drgdata,[3 2 1]); %rotating drgdata dims %***
% Manipulating CL values for x-axis
xdatacl=zeros(numbcls+1); %***
xdatacl=(MASTDRG(1,:)/10); %***
xdatacl(1)=[]; %***
% Plot drag breakdown for each mach number %***
for j=1:1:numbmhs %***
figure(30+j) %***
grid on;
drgdats=(squeeze(drgdata(:,:,j)))'; %*** taking 2D Mach number slices of 3D drgdata matrix
%colormap(bone)
bar(xdatacl,drgdats,1.5) %*** producing grouped column plot of CL vs. CD (counts)
title(['Mach ',num2str(MASTDRG(j+1,1)/10)]) %***
xlabel('C_L') %***
ylabel('Drag (Counts)') %***
legend('Vor-Ind_w','Zero-Lift','Profile','Trim','Comp','Location','NorthWest','Orientation','horizontal') %***
end %***
%end %drgplot function %***
case 12 %***
disp('""""""""""""""""""""""""""""""""""""""""""""""""""""""');
disp('Available polar breakdown result files are: ')
ls([settings.odir,'/','*-Cx_drgout.mat'])
data=questions(10);
try %***
fname=strcat(data,'-Cx_drgout'); %*** alternative
load([settings.odir,'/', fname]);
catch %***