How to make different character for each legend in my code?

Hi everyone,

I am trying to give each line different legend charcter like * or o to distinguish better among them.

I am asking about the case when k>3.

could you please help me about this. thanks

like the legend shapes as shown here

https://www.mathworks.com/matlabcentral/fileexchange/66464-gridlegend

close all
clear all
clc

%%% Fixed Parameters

B = 2;                                  % Number of Blades
R = 10.06;                              % Blade Radius in meter
Rho = 1.225;                            % Density of air kg/m3
w = 7.501;                              % Rotational Speed rad/s
Theta_P = -3;                           % Tip Pitch Angle in degree
ac = 0.2;                               % Glauert correction
eps = 1e-5;                             % Error tolerance

nc=1:1:16;                              % number of configurations for effect off different distribution
%%%  Airfoil Date 
afoil = readmatrix('airfoil data5e5.xlsx');
Aoa = afoil(:,1);
Cl = afoil(:,2);
Cd = afoil(:,3);
Velocity =[5,6,7,8,9,11];               % Wind Speed  m/s
MTotal=[];

%%%  Torque vs Velocity Data 
      
torquee = readmatrix('TorqueWindSpeedExperi.xlsx');
vupper=torquee(1:5,1);                  % Radial Distance in meter
vlower=torquee(6:10,1);                 % Chord length in meter
torquelower=torquee(1:5,2);             % Twist  in degree
torqueupper=torquee(6:10,2);

%%% Given Blade Data

sections = readmatrix('chord and twist 15 distributions.xlsx');
iter=0;
for k=3:2:33
    
    iter=iter+1;                % used in legends in plots      
    
    r=sections(1:26,2);                        % Radial Distance in meter
    SS=sections(1:26,3);                       % Span Station %
    Chord=sections(1:26,k+1);                    % Chord length in meter
    Beta=sections(1:26,k+2);                     % Twist  in degree

for j=1:length(Velocity)
    
for i = 8:length(r)
    
sigma(i) = (B*Chord(i))/(2*pi*r(i)); 

a=0;
a_prime=0;

alist(i)=[0];
alistprime(i)=[0];

for n=1:1000
    
Phi =  atand(((1-a)*Velocity(j))/((1+a_prime)*w*r(i)));  % Flow Angle     

Theta = Beta(i) + Theta_P ;

aoa = Phi- Theta;                  % local angle of attack in degree

f = (B/2)* ((R-r(i))/(r(i)*sind(Phi)));
F = (2/pi)*acos(exp(-f));           % Prandtl correction factor 

cl=interp1(Aoa,Cl,aoa,'linear','extrap');
cd=interp1(Aoa,Cd,aoa,'linear','extrap');

Cn = cl*cosd(Phi)+cd*sind(Phi);
Ct =cl*sind(Phi)-cd*cosd(Phi);

K=(4*F*(sind(Phi))^2)/(sigma(i)*Cn);

%%%%%%%%%% a and ac condition
    
a = 1/(((4*F*(sind(Phi)^2))/(sigma(i)*Cn))+1);

if a < ac || a==ac
a=a;
else
a = 0.5*(2+K*(1-2*ac)-sqrt(((K*(1-2*ac)+2)^2)+4*((K*(ac^2))-1)));
end

a_prime =1/(((4*F*(sind(Phi)*cosd(Phi)))/(sigma(i)*Ct))-1);

alist(i,n+1)=a;           
alistprime(i,n+1)=a_prime;

%%% condition for epsilon or tolerance

if a-alist(i,n) < eps && a_prime-alistprime(i,n) < eps
    break;
end

end

%%% V relative 
v_rel(i) = sqrt( (Velocity(j)*(1-alist(end)))^2 + (w*r(i)*(1+alistprime(end)))^2 ); 

%%%  The tangential force per length Pt
Pt(i) = 0.5*Rho*(v_rel(i)^2)*Chord(i)*Ct;

end


for i=8:length(Pt)-1
         
Ai(i) = (Pt(i+1)-Pt(i) ) / (r(i+1)-r(i));
        
Bi(i) = ((Pt(i)*r(i+1))-(Pt(i+1)*r(i)) ) / (r(i+1)-r(i));

Pt_total(i) =  Ai(i)*r(i)+Bi(i);

end
      
    

for i=8:length(Pt)-1
    
M(i) = ((1/3)*Ai(i)*((r(i+1)^3)-(r(i)^3))) + ((0.5)*Bi(i)*((r(i+1)^2)-(r(i)^2)));    
end     

% % total shaft torque and power
MTotal(j) = B* sum(M);
Power(j)=MTotal(j)*w*1e-3;

    if k==3
       TorqueBaseline=MTotal; 
    end


end

    if k==3

    figure(1)
    hold on
    leg = sprintf(' Baseline ');
    plot(Velocity,MTotal,'-oblack','LineWidth',1.5, 'displayname', leg);  grid on


    end

    if k>3

    figure(1)
    hold on
    leg = sprintf('config %g',nc(iter)-1);
    plot(Velocity,MTotal, 'displayname', leg);  grid on
    xlabel(' Wind Speed (m/s) '); ylabel(' Torque (Nm)  ');
    set(gca,'XTick',(4:1:20)); set(gca,'YTick',(0:300:1800))
    ylim([0 1800]); xlim([4 20]);

    end
    
    if k==33
        figure(1)
        hold on
        leg = sprintf('Experimental upper range ');
        plot(vupper,torqueupper,'-or','LineWidth',1.5, 'displayname', leg)
        
        figure(1)
        hold on
        leg = sprintf('Experimental lower range ');
        plot(vlower,torquelower,'-or','LineWidth',1.5,'displayname', leg)
        
    end
    
    for i =1
        if Aoa(i)>-19
            title(' Reynolds number = 500.000' )
        else
            title(' Reynolds number = 1.000.000' )
        end
    end

end

legend show

Answer 1

[Cris LaPierre]

Markers in your legend come from the linespec used when plotting your line. Plot each line with a different marker style. MATLAB has 15 markers to pick from.

Somewhere in your code before the for loop define the markers:

mrkr = 'o+*.x_|sd^v><ph';

and then when you plot, add a marker style to your code

plot(Velocity,MTotal,"Marker",mrkr(nc(iter)-1),'displayname', leg);

This will only work if you have <=15 lines to plot.

[mehmet salihi]

firstly, Thank you very much for your help.

the code and the markers are working, but the legend list does not exist in the figure.

I can not know which marker for which configuration.

could you please check it one more again.

[mehmet salihi]

I solve it, thanks one more again.

[Cris LaPierre]

Did you leave off the code for the legend?

%%% Fixed Parameters
B = 2;                                  % Number of Blades
R = 10.06;                              % Blade Radius in meter
Rho = 1.225;                            % Density of air kg/m3
w = 7.501;                              % Rotational Speed rad/s
Theta_P = -3;                           % Tip Pitch Angle in degree
ac = 0.2;                               % Glauert correction
eps = 1e-5;                             % Error tolerance
mrkr = 'o+*.x_|sd^v><ph';

nc=1:1:16;                              % number of configurations for effect off different distribution
%%%  Airfoil Date
afoil = readmatrix('airfoil data5e5.xlsx');
Aoa = afoil(:,1);
Cl = afoil(:,2);
Cd = afoil(:,3);
Velocity =[5,6,7,8,9,11];               % Wind Speed  m/s
MTotal=[];

%%%  Torque vs Velocity Data
torquee = readmatrix('TorqueWindSpeedExperi.xlsx');
vupper=torquee(1:5,1);                  % Radial Distance in meter
vlower=torquee(6:10,1);                 % Chord length in meter
torquelower=torquee(1:5,2);             % Twist  in degree
torqueupper=torquee(6:10,2);

%%% Given Blade Data
sections = readmatrix('chord and twist 15 distributions.xlsx');
iter=0;
for k=3:2:33
    iter=iter+1;                % used in legends in plots

    r=sections(1:26,2);                        % Radial Distance in meter
    SS=sections(1:26,3);                       % Span Station %
    Chord=sections(1:26,k+1);                    % Chord length in meter
    Beta=sections(1:26,k+2);                     % Twist  in degree

    for j=1:length(Velocity)
        for i = 8:length(r)

            sigma(i) = (B*Chord(i))/(2*pi*r(i));

            a=0;
            a_prime=0;

            alist(i)=[0];
            alistprime(i)=[0];

            for n=1:1000
                Phi =  atand(((1-a)*Velocity(j))/((1+a_prime)*w*r(i)));  % Flow Angle

                Theta = Beta(i) + Theta_P ;

                aoa = Phi- Theta;                  % local angle of attack in degree

                f = (B/2)* ((R-r(i))/(r(i)*sind(Phi)));
                F = (2/pi)*acos(exp(-f));           % Prandtl correction factor

                cl=interp1(Aoa,Cl,aoa,'linear','extrap');
                cd=interp1(Aoa,Cd,aoa,'linear','extrap');

                Cn = cl*cosd(Phi)+cd*sind(Phi);
                Ct =cl*sind(Phi)-cd*cosd(Phi);

                K=(4*F*(sind(Phi))^2)/(sigma(i)*Cn);

                %%%%%%%%%% a and ac condition

                a = 1/(((4*F*(sind(Phi)^2))/(sigma(i)*Cn))+1);

                if a < ac || a==ac
                    a=a;
                else
                    a = 0.5*(2+K*(1-2*ac)-sqrt(((K*(1-2*ac)+2)^2)+4*((K*(ac^2))-1)));
                end

                a_prime =1/(((4*F*(sind(Phi)*cosd(Phi)))/(sigma(i)*Ct))-1);

                alist(i,n+1)=a;
                alistprime(i,n+1)=a_prime;

                %%% condition for epsilon or tolerance

                if a-alist(i,n) < eps && a_prime-alistprime(i,n) < eps
                    break;
                end

            end

            %%% V relative
            v_rel(i) = sqrt( (Velocity(j)*(1-alist(end)))^2 + (w*r(i)*(1+alistprime(end)))^2 );

            %%%  The tangential force per length Pt
            Pt(i) = 0.5*Rho*(v_rel(i)^2)*Chord(i)*Ct;

        end

        for i=8:length(Pt)-1
            Ai(i) = (Pt(i+1)-Pt(i) ) / (r(i+1)-r(i));

            Bi(i) = ((Pt(i)*r(i+1))-(Pt(i+1)*r(i)) ) / (r(i+1)-r(i));

            Pt_total(i) =  Ai(i)*r(i)+Bi(i);

        end

        for i=8:length(Pt)-1
            M(i) = ((1/3)*Ai(i)*((r(i+1)^3)-(r(i)^3))) + ((0.5)*Bi(i)*((r(i+1)^2)-(r(i)^2)));
        end

        % % total shaft torque and power
        MTotal(j) = B* sum(M);
        Power(j)=MTotal(j)*w*1e-3;

        if k==3
            TorqueBaseline=MTotal;
        end
    end

    if k==3
        figure(1)
        hold on
        leg = sprintf(' Baseline ');
        plot(Velocity,MTotal,'-oblack','LineWidth',1.5, 'displayname', leg);  grid on

    end

    if k>3
        figure(1)
        hold on
        leg = sprintf('config %g',nc(iter)-1);
        plot(Velocity,MTotal,"Marker",mrkr(nc(iter)-1),'displayname', leg);  grid on
        xlabel(' Wind Speed (m/s) '); ylabel(' Torque (Nm)  ');
        set(gca,'XTick',(4:1:20)); set(gca,'YTick',(0:300:1800))
        ylim([0 1800]); xlim([4 20]);

    end

    if k==33
        figure(1)
        hold on
        leg = sprintf('Experimental upper range ');
        plot(vupper,torqueupper,'-or','LineWidth',1.5, 'displayname', leg)

        figure(1)
        hold on
        leg = sprintf('Experimental lower range ');
        plot(vlower,torquelower,'-or','LineWidth',1.5,'displayname', leg)

    end

    for i =1
        if Aoa(i)>-19
            title(' Reynolds number = 500.000' )
        else
            title(' Reynolds number = 1.000.000' )
        end
    end

end

legend show

Answer 2

[Voss]

close all
clear all
clc

%%% Fixed Parameters

B = 2;                                  % Number of Blades
R = 10.06;                              % Blade Radius in meter
Rho = 1.225;                            % Density of air kg/m3
w = 7.501;                              % Rotational Speed rad/s
Theta_P = -3;                           % Tip Pitch Angle in degree
ac = 0.2;                               % Glauert correction
eps = 1e-5;                             % Error tolerance

nc=1:1:16;                              % number of configurations for effect off different distribution
%%%  Airfoil Date 
afoil = readmatrix('airfoil data5e5.xlsx');
Aoa = afoil(:,1);
Cl = afoil(:,2);
Cd = afoil(:,3);
Velocity =[5,6,7,8,9,11];               % Wind Speed  m/s
MTotal=[];

%%%  Torque vs Velocity Data 
      
torquee = readmatrix('TorqueWindSpeedExperi.xlsx');
vupper=torquee(1:5,1);                  % Radial Distance in meter
vlower=torquee(6:10,1);                 % Chord length in meter
torquelower=torquee(1:5,2);             % Twist  in degree
torqueupper=torquee(6:10,2);

%%% Given Blade Data

sections = readmatrix('chord and twist 15 distributions.xlsx');
iter=0;


n_lines = (33-3)/2+1;
all_markers = '+*.xsd^v><pho';
all_markers = repmat(all_markers,1,ceil(n_lines/numel(all_markers)));
my_markers = repmat(' ',1,33);
my_markers(3:2:33) = all_markers(1:n_lines);


for k=3:2:33
    
    iter=iter+1;                % used in legends in plots      
    
    r=sections(1:26,2);                        % Radial Distance in meter
    SS=sections(1:26,3);                       % Span Station %
    Chord=sections(1:26,k+1);                    % Chord length in meter
    Beta=sections(1:26,k+2);                     % Twist  in degree
    
    for j=1:length(Velocity)
        
        for i = 8:length(r)
            
            sigma(i) = (B*Chord(i))/(2*pi*r(i)); 
            
            a=0;
            a_prime=0;
            
            alist(i)=[0];
            alistprime(i)=[0];
            
            for n=1:1000
                
                Phi =  atand(((1-a)*Velocity(j))/((1+a_prime)*w*r(i)));  % Flow Angle     
                
                Theta = Beta(i) + Theta_P ;
                
                aoa = Phi- Theta;                  % local angle of attack in degree
                
                f = (B/2)* ((R-r(i))/(r(i)*sind(Phi)));
                F = (2/pi)*acos(exp(-f));           % Prandtl correction factor 
                
                cl=interp1(Aoa,Cl,aoa,'linear','extrap');
                cd=interp1(Aoa,Cd,aoa,'linear','extrap');
                
                Cn = cl*cosd(Phi)+cd*sind(Phi);
                Ct =cl*sind(Phi)-cd*cosd(Phi);
                
                K=(4*F*(sind(Phi))^2)/(sigma(i)*Cn);
                
                %%%%%%%%%% a and ac condition
                
                a = 1/(((4*F*(sind(Phi)^2))/(sigma(i)*Cn))+1);
                
                if a < ac || a==ac
                    a=a;
                else
                    a = 0.5*(2+K*(1-2*ac)-sqrt(((K*(1-2*ac)+2)^2)+4*((K*(ac^2))-1)));
                end
                
                a_prime =1/(((4*F*(sind(Phi)*cosd(Phi)))/(sigma(i)*Ct))-1);
                
                alist(i,n+1)=a;           
                alistprime(i,n+1)=a_prime;
                
                %%% condition for epsilon or tolerance
                
                if a-alist(i,n) < eps && a_prime-alistprime(i,n) < eps
                    break;
                end
                
            end
            
            %%% V relative 
            v_rel(i) = sqrt( (Velocity(j)*(1-alist(end)))^2 + (w*r(i)*(1+alistprime(end)))^2 ); 
            
            %%%  The tangential force per length Pt
            Pt(i) = 0.5*Rho*(v_rel(i)^2)*Chord(i)*Ct;
            
        end
        
        
        for i=8:length(Pt)-1
            
            Ai(i) = (Pt(i+1)-Pt(i) ) / (r(i+1)-r(i));
            
            Bi(i) = ((Pt(i)*r(i+1))-(Pt(i+1)*r(i)) ) / (r(i+1)-r(i));
            
            Pt_total(i) =  Ai(i)*r(i)+Bi(i);
            
        end
        
        
        
        for i=8:length(Pt)-1
            
            M(i) = ((1/3)*Ai(i)*((r(i+1)^3)-(r(i)^3))) + ((0.5)*Bi(i)*((r(i+1)^2)-(r(i)^2)));    
        end     
        
        % % total shaft torque and power
        MTotal(j) = B* sum(M);
        Power(j)=MTotal(j)*w*1e-3;
        
        if k==3
            TorqueBaseline=MTotal; 
        end
        
        
    end
    
    if k==3
        
        figure(1)
        hold on
        leg = sprintf(' Baseline ');
        plot(Velocity,MTotal,'-oblack','LineWidth',1.5, 'displayname', leg);  grid on
        
        
    end
    
    if k>3
        
        figure(1)
        hold on
        leg = sprintf('config %g',nc(iter)-1);
        
%         plot(Velocity,MTotal, 'displayname', leg);  grid on
        plot(Velocity,MTotal,[my_markers(k) '-'], 'displayname', leg);  grid on
        
        xlabel(' Wind Speed (m/s) '); ylabel(' Torque (Nm)  ');
        set(gca,'XTick',(4:1:20)); set(gca,'YTick',(0:300:1800))
        ylim([0 1800]); xlim([4 20]);
        
    end
    
    if k==33
        figure(1)
        hold on
        leg = sprintf('Experimental upper range ');
        plot(vupper,torqueupper,'-or','LineWidth',1.5, 'displayname', leg)
        
        figure(1)
        hold on
        leg = sprintf('Experimental lower range ');
        plot(vlower,torquelower,'-or','LineWidth',1.5,'displayname', leg)
        
    end
    
    for i =1
        if Aoa(i)>-19
            title(' Reynolds number = 500.000' )
        else
            title(' Reynolds number = 1.000.000' )
        end
    end

end

legend show

[mehmet salihi]

thank you for your help

Answer 3

[Sulaymon Eshkabilov]

There are a few different ways to do that. But before jumping to the plot options, in your code some of the loops can be eliminated to enahce the computation time, e.g.:

This loop:

for i=8:length(Pt)-1

Ai(i) = (Pt(i+1)-Pt(i) ) / (r(i+1)-r(i));

Bi(i) = ((Pt(i)*r(i+1))-(Pt(i+1)*r(i)) ) / (r(i+1)-r(i));

Pt_total(i) = Ai(i)*r(i)+Bi(i);

end

for i=8:length(Pt)-1

M(i) = ((1/3)*Ai(i)*((r(i+1)^3)-(r(i)^3))) + ((0.5)*Bi(i)*((r(i+1)^2)-(r(i)^2)));

end

Can be substituted with:

N = length(Pt);

Ai = diff(Pt(8:N))./(diff(r(8:N).'));

Bi = ((Pt(8:N-1).*(r(9:N).'))-(Pt(9:N).*(r(8:N-1).')))./(diff(r(8:N).'));

Pt_total = Ai.*(r(8:N-1).')+Bi;

M = ((1/3)*Ai.*((r(9:N).^3).'-(r(8:N-1).^3).')) + ((0.5)*Bi.*((r(9:N).^2).'-(r(8:N-1).^2).'));

Now, how to get nice looking legends and here is the complete code:

close all; clearvars; clc

%%% Fixed Parameters

B = 2;                                  % Number of Blades
R = 10.06;                              % Blade Radius in meter
Rho = 1.225;                            % Density of air kg/m3
w = 7.501;                              % Rotational Speed rad/s
Theta_P = -3;                           % Tip Pitch Angle in degree
ac = 0.2;                               % Glauert correction
eps = 1e-5;                             % Error tolerance

nc=1:1:16;                              % number of configurations for effect off different distribution
%%%  Airfoil Date 
afoil = readmatrix('airfoil data5e5.xlsx');
Aoa = afoil(:,1);
Cl = afoil(:,2);
Cd = afoil(:,3);
Velocity =[5,6,7,8,9,11];               % Wind Speed  m/s
MTotal=[];

%%%  Torque vs Velocity Data 
      
torquee = readmatrix('TorqueWindSpeedExperi.xlsx');
vupper=torquee(1:5,1);                  % Radial Distance in meter
vlower=torquee(6:10,1);                 % Chord length in meter
torquelower=torquee(1:5,2);             % Twist  in degree
torqueupper=torquee(6:10,2);

%%% Given Blade Data

sections = readmatrix('chord and twist 15 distributions.xlsx');
iter=0;
for k=3:2:33
    
    iter=iter+1;                % used in legends in plots      
    
    r=sections(1:26,2);                        % Radial Distance in meter
    SS=sections(1:26,3);                       % Span Station %
    Chord=sections(1:26,k+1);                    % Chord length in meter
    Beta=sections(1:26,k+2);                     % Twist  in degree

for j=1:length(Velocity)
    
for i = 8:length(r)
    
sigma(i) = (B*Chord(i))/(2*pi*r(i)); 

a=0;
a_prime=0;

alist(i)=[0];
alistprime(i)=[0];

for n=1:1000
    
Phi =  atand(((1-a)*Velocity(j))/((1+a_prime)*w*r(i)));  % Flow Angle     

Theta = Beta(i) + Theta_P ;

aoa = Phi- Theta;                  % local angle of attack in degree

f = (B/2)* ((R-r(i))/(r(i)*sind(Phi)));
F = (2/pi)*acos(exp(-f));           % Prandtl correction factor 

cl=interp1(Aoa,Cl,aoa,'linear','extrap');
cd=interp1(Aoa,Cd,aoa,'linear','extrap');

Cn = cl*cosd(Phi)+cd*sind(Phi);
Ct =cl*sind(Phi)-cd*cosd(Phi);

K=(4*F*(sind(Phi))^2)/(sigma(i)*Cn);

%%%%%%%%%% a and ac condition
    
a = 1/(((4*F*(sind(Phi)^2))/(sigma(i)*Cn))+1);

if a < ac || a==ac
a=a;
else
a = 0.5*(2+K*(1-2*ac)-sqrt(((K*(1-2*ac)+2)^2)+4*((K*(ac^2))-1)));
end

a_prime =1/(((4*F*(sind(Phi)*cosd(Phi)))/(sigma(i)*Ct))-1);

alist(i,n+1)=a;           
alistprime(i,n+1)=a_prime;

%%% condition for epsilon or tolerance

if a-alist(i,n) < eps && a_prime-alistprime(i,n) < eps
    break;
end

end

%%% V relative 
v_rel(i) = sqrt( (Velocity(j)*(1-alist(end)))^2 + (w*r(i)*(1+alistprime(end)))^2 ); 

%%%  The tangential force per length Pt
Pt(i) = 0.5*Rho*(v_rel(i)^2)*Chord(i)*Ct;

end


      
N = length(Pt); 
Ai = diff(Pt(8:N))./(diff(r(8:N).'));
Bi = ((Pt(8:N-1).*(r(9:N).'))-(Pt(9:N).*(r(8:N-1).')))./(diff(r(8:N).'));
Pt_total =  Ai.*(r(8:N-1).')+Bi;    

M = ((1/3)*Ai.*((r(9:N).^3).'-(r(8:N-1).^3).')) + ((0.5)*Bi.*((r(9:N).^2).'-(r(8:N-1).^2).'));    

% % total shaft torque and power
MTotal(j) = B* sum(M);
Power(j)=MTotal(j)*w*1e-3;

    if k==3
       TorqueBaseline=MTotal; 
    end
end

    if k==3
    figure(1)
    hold on
    leg = sprintf(' Baseline ');
    plot(Velocity,MTotal,'-oblack','LineWidth',1.5, 'displayname', leg);  grid on

    end
CC = 'rgbmkcgbgmcmrgbkm'; % Color Selection for lines and markerfaces
LL = '-:--';              % Line Type 
MM = 'odphs<>^';          % Marker Type 

    if k>3
    leg = sprintf('config %g',nc(iter)-1);
    Ls=randi(numel(LL),1);    % Random selection of Line Type
    Ms=randi(numel(MM),1);     % Random selection of Marker Type
    CLs=randi(numel(CC),1);     % Random selection of Line Color 
    CMs=randi(numel(CC),1);      % Random selection of Marker Face Color 

   LMC =[CC(CLs) LL(Ls) MM(Ms)];
    plot(Velocity,MTotal, LMC, 'markerfacecolor', CC(CMs), 'displayname', leg);  grid on
    xlabel(' Wind Speed (m/s) '); ylabel(' Torque (Nm)  ');
    set(gca,'XTick',(4:1:20)); set(gca,'YTick',(0:300:1800))
    ylim([0 1800]); xlim([4 20]);
    end
    
    if k==33
        leg = sprintf('Experimental upper range ');
        plot(vupper,torqueupper,'-or','LineWidth',1.5, 'displayname', leg)
        
        leg = sprintf('Experimental lower range ');
        plot(vlower,torquelower,'-or','LineWidth',1.5,'displayname', leg)
        
    end
    
    for i =1
        if Aoa(i)>-19
            title(' Reynolds number = 500.000' )
        else
            title(' Reynolds number = 1.000.000' )
        end
    end

end

legend show

[Cris LaPierre]

Modified your post slightly so the code could be run here.

[mehmet salihi]

I really like to thank you for your help and showing me the best ways to code better taking into account the computation time.

I appreciate it really.

In addition, the way for legends are perfect.

once more time thank you my friend.

[Sulaymon Eshkabilov]

Most welcome! Glad to be of some help.