Plotting graph with for-end loop in

How do i plot a graph of the data in the for-end loop.

Looking to plot a varying Vf against Ex,Ey,Gxy,vxy.

>> %Setting all original variables
Em=2.4e9; 
Ef=76e9;
vm=0.34;
vf=0.22;
theta=30;
for Vf=0:0.1:1
Vm=1-Vf;


%Finding shear and bulk modulus'
Gm=Em/(2*(1+vm));
Gf=Ef/(2*(1+vf));
Km=Em/(3*(1-2*vm));
Kf=Ef/(3*(1-2*vf));

%Find k*,E1,v12,G12
k=(Km*(Kf+Gm)*Vm+Kf*(Km+Gm)*Vf)/((Kf+Gm)*Vm+(Km+Gm)*Vf);
E1=Em*Vm+Ef*Vf;
v12=vm*Vm+vf*Vf+((vf-vm)*((1/Km)-(1/Kf))*Vm*Vf)/((Vm/Kf)+(Vf/Km)+(1/Gm));
G12=Gm+(Vf/((1/(Gf-Gm))+(Vm/(2*Gm))));

%Beta's, gamma's, alphas and roe
betam=1/(3-4*vm);
betaf=1/(3-4*vf);
gamma=Gf/Gm;
alpha=(betam-gamma*betaf)/(1+gamma*betaf);
roe=(gamma+betam)/(gamma-1);

%G23, E2 and v23
G23=Gm*(1+((1+betam)*Vf)/(roe-(1+(3*betam^2*Vm^2)/(alpha*Vf^3+1))*Vf));
E2=4/((1/G23)+(1/k)+(4*v12^2/E1));
v23=(E2/2*G23)-1;

%Creating reduced lamina stiffness matrix
Z=(E1-v12^2*E2)/E1;
Q11=E1/Z;
Q22=E2/Z;
Q12=v12*E2/Z;
Q66=G12;
Q=[Q11,Q12,0;Q12,Q22,0;0,0,Q66];

%Transformation matrices
n=sind(theta);
m=cosd(theta);
q11=Q11*m^4+Q22*n^4+2*m^2*n^2*(Q12+2*Q66);
q12=m^2*n^2*(Q11+Q22-4*Q66)+(m^4+n^4)*Q12;
q16=(Q11*m^2-Q22*n^2-(Q12+2*Q66)*(m^2-n^2))*m*n;
q22=Q11*n^4+Q22*m^4+2*m^2*n^2*(Q12+2*Q66);
q26=(Q11*n^2-Q22*m^2+(Q12+2*Q66)*(m^2-n^2))*m*n;
q66=(Q11+Q22+Q12*2)*m^2*n^2+Q66*((m^2-n^2)^2);
q=[q11,q12,q16;q12,q22,q26;q16,q26,q66];

%Finally calculating the laminate properties
Ex=q11-q12^2/q22
Ey=q22-q12^2/q11
Gxy=q66
vxy=q12/q22

end

Answer 1

[Bhaskar R]

%Setting all original variables
Em=2.4e9;
Ef=76e9;
vm=0.34;
vf_samll=0.22;
theta=30;
Vf=0:0.1:1;
Ex = zeros(1, length(Vf));
Ey = zeros(1, length(Vf));
Gxy = zeros(1, length(Vf));
vxy = zeros(1, length(Vf));
c = 1;
for ii = 1:length(Vf)
    Vm=1-Vf(ii);
    
    
    %Finding shear and bulk modulus'
    Gm=Em/(2*(1+vm));
    Gf=Ef/(2*(1+vf_samll));
    Km=Em/(3*(1-2*vm));
    Kf=Ef/(3*(1-2*vf_samll));
    
    %Find k*,E1,v12,G12
    k=(Km*(Kf+Gm)*Vm+Kf*(Km+Gm)*Vf(ii))/((Kf+Gm)*Vm+(Km+Gm)*Vf(ii));
    E1=Em*Vm+Ef*Vf(ii);
    v12=vm*Vm+vf_samll*Vf(ii)+((vf_samll-vm)*((1/Km)-(1/Kf))*Vm*Vf(ii))/((Vm/Kf)+(Vf(ii)/Km)+(1/Gm));
    G12=Gm+(Vf(ii)/((1/(Gf-Gm))+(Vm/(2*Gm))));
    
    %Beta's, gamma's, alphas and roe
    betam=1/(3-4*vm);
    betaf=1/(3-4*vf_samll);
    gamma=Gf/Gm;
    alpha=(betam-gamma*betaf)/(1+gamma*betaf);
    roe=(gamma+betam)/(gamma-1);
    
    %G23, E2 and v23
    G23=Gm*(1+((1+betam)*Vf(ii))/(roe-(1+(3*betam^2*Vm^2)/(alpha*Vf(ii)^3+1))*Vf(ii)));
    E2=4/((1/G23)+(1/k)+(4*v12^2/E1));
    v23=(E2/2*G23)-1;
    
    %Creating reduced lamina stiffness matrix
    Z=(E1-v12^2*E2)/E1;
    Q11=E1/Z;
    Q22=E2/Z;
    Q12=v12*E2/Z;
    Q66=G12;
    Q=[Q11,Q12,0;Q12,Q22,0;0,0,Q66];
    
    %Transformation matrices
    n=sind(theta);
    m=cosd(theta);
    q11=Q11*m^4+Q22*n^4+2*m^2*n^2*(Q12+2*Q66);
    q12=m^2*n^2*(Q11+Q22-4*Q66)+(m^4+n^4)*Q12;
    q16=(Q11*m^2-Q22*n^2-(Q12+2*Q66)*(m^2-n^2))*m*n;
    q22=Q11*n^4+Q22*m^4+2*m^2*n^2*(Q12+2*Q66);
    q26=(Q11*n^2-Q22*m^2+(Q12+2*Q66)*(m^2-n^2))*m*n;
    q66=(Q11+Q22+Q12*2)*m^2*n^2+Q66*((m^2-n^2)^2);
    q=[q11,q12,q16;q12,q22,q26;q16,q26,q66];
    
    %Finally calculating the laminate properties
    Ex(c)=q11-q12^2/q22;
    Ey(c)=q22-q12^2/q11;
    Gxy(c)=q66;
    vxy(c)=q12/q22;
    c =c+1;
end
plot(Vf, Ex, Vf, Ey, Vf, Gxy, Vf, vxy);
grid on , legend({'Ex', 'Ey', 'Gxy', 'vxy'})

[Peter Kinsley]

that works, thanks.