Plotting a symbolic vector

I want to plot the shear and bending moment diagrams for a wing at diffrent load cases, given a symbolic vector for the lift distribution. I want to get something like this:

Is there a way I can do this?

Thank you!

Here is my script

clc 
clear all
close all

%% Code for generating shear and bending moment diagrams for a wing generating lift at different load cases

b=3.75; % Wing span (m)
S=3.55; % wing area (m^2)
r=0.5; % Taper
Cr=1.27; %Root chord (m)
MAC=0.97; %Mean aerodynamic chord (m)
m_AO=15;  %Wing mass
G=m_AO*9.81; %Wing weight
n1=3.8;  %Load factor

%Total lift generated by wing for different load cases (N):
L=[890.19 1021.01 1279.12 -1935.61 -2267.18 -3242.27 2303.19 2665.21 3539.82 -3348.61 -3911.38 -5502.97]/2;  

syms x

c=Cr*(1+2*(r-1)/b*x);  %Chord distribution along wing 
g_AO=n1*(G/b*c/MAC);   %Wing weight distribution along wing

L_sch= L.*((Cr*(1+2*x/b*(r-1)))+((4/pi)*MAC*sqrt(1-(2*x/b).^2)))/2;  %Vector for Schrenk lift distribution along wing

Tz=piecewise(x>0, int((L_sch-g_AO),x,x,b/2)); %Shear force symbolic vector
Mx=piecewise(x>0, int(-Tz,x,x,b/2));          %Bending moment symbolic vector


figure
plot(Tz, [0 b/2],linewidth=2)
title 'Shear force diagram'
ylabel('T_z [N]')
xlabel('Locația în semi-anvergură [m]')
grid on
box off

figure
fplot(Mx, [0,b/2],linewidth=2,Color='#D95319')
title 'Bending moment diagram'
ylabel('M_x [Nm]')
xlabel('Locația în semi-anvergură [m]')
grid on
box off

Answer 1

[Dyuman Joshi]

You can remove the piecewise definition and use fplot from [0 b/2], then adjust the xlimits (and xticks) accordingly

clc 
clear all
close all

%% Code for generating shear and bending moment diagrams for a wing generating lift at different load cases

b=3.75; % Wing span (m)
S=3.55; % wing area (m^2)
r=0.5; % Taper
Cr=1.27; %Root chord (m)
MAC=0.97; %Mean aerodynamic chord (m)
m_AO=15;  %Wing mass
G=m_AO*9.81; %Wing weight
n1=3.8;  %Load factor

%Total lift generated by wing for different load cases (N):
L=[890.19 1021.01 1279.12 -1935.61 -2267.18 -3242.27 2303.19 2665.21 3539.82 -3348.61 -3911.38 -5502.97]/2;  

syms x

c=Cr*(1+2*(r-1)/b*x);  %Chord distribution along wing 
g_AO=n1*(G/b*c/MAC);   %Wing weight distribution along wing

L_sch= L.*((Cr*(1+2*x/b*(r-1)))+((4/pi)*MAC*sqrt(1-(2*x/b).^2)))/2;  %Vector for Schrenk lift distribution along wing

Tz=int((L_sch-g_AO),x,x,b/2);
%Shear force symbolic vector
Mx=int(-Tz,x,x,b/2);          %Bending moment symbolic vector
figure
fplot(Tz, [0 b/2], '-.', 'LineWidth', 1.5) %%Added line style and modified line width
title 'Shear force diagram'
ylabel('T_z [N]')
xlabel('Locația în semi-anvergură [m]')
grid on
box off
%You can similarly modify ylimits and yticks as required
xlim([-0.25 2])
xticks(-0.25:0.25:2)

figure
fplot(Mx, [0,b/2],linewidth=2,Color='#D95319')
title 'Bending moment diagram'
ylabel('M_x [Nm]')
xlabel('Locația în semi-anvergură [m]')
grid on
box off
xlim([-0.25 2])
xticks(-0.25:0.25:2)

[Gavril Birsanu]

Thank you very much for the quick response! Much appreciated!

[Dyuman Joshi]

You are welcome!