Help plotting a graph

I'm trying to plot C_We vs pi_c. However, my graph is not showing up. I'm not sure if I'm using the wrong symbols but I need help with how to get my results to show. I'm just seeing a blank figure.

% Given
Ma=0.44
deltaH=17940;
W_cp=0.97;
P_a=12.93252;
m_dot=26;
T_t4=2150;
T_a=506.21;
gamma=1.4;
R=53.35;
Cp=0.2399565;
rho_8= 7.952636E-04;

% Diffuser
a_a=sqrt(gamma*R*32.17*T_a)
u_a=Ma*a_a
Tta_Ta=(1+0.5*(gamma-1).*Ma^2)
T_ta=506.21 * 1.03872
T_t2=T_ta
Pta_Pa=(Tta_Ta)^((gamma)/(gamma-1))
Pt2_Pa=Pta_Pa
P_t2=Pta_Pa*P_a

%Compressor
P_t3=pi_c*P_t2
tau_c=pi_c^((gamma-1)/gamma)
T_t3=tau_c*T_t2

%Primary Combustor

P_t4=P_t3
m_dotf=(m_dot*Cp*(T_t4-T_t3))/ deltaH

%Turbine
 T_t5=(((m_dot*Cp*(T_t3-T_t2)+W_cp*m_dot*Cp*T_a)/(m_dot*Cp))-T_t4)*-1
 tau_t=T_t5/T_t4
 pi_t= 0.2157084
 P_t5=pi_t*P_t4

 %Primary Nozzle
 T_t6=T_t5
 P_t6=P_t5
 P_8= 12.93252 %exit pressure matches ambient pressure
 T_8=T_t6*((P_8/P_t6)^((gamma-1)/gamma))
 u_8=[2*Cp*(T_t6-T_8)*32.17*778.16]^0.5
 a_8=(gamma*R*T_8*32.17)^0.5
 M_8=u_8/a_8
 A_8=m_dot*144/(rho_8*u_8*32.17)

% Function for the work coefficient
tau_5=(T_ta/T_a)*tau_c*tau_t;
a=T_t4/T_a
b=T_ta/T_a
c=T_a/T_ta
d=[((a*c*((tau_t-1)/tau_c))/b-1)^(0.5)-1]

C_we=(a*(1-(tau_5/(b*tau_c)))-(b*(tau_c-1)))+((gamma-1)*(Ma^2)*((((a*c*((tau_5-1)/tau_c))/(b-1))^(0.5))-1))

%% Graph

% 1. Cwe vs pi_c
f1=figure(1);clf;

C_we=(a*(1-(tau_5/(b*tau_c)))-(b*(tau_c-1)))+((gamma-1)*(Ma^2)*((((a*c*((tau_5-1)/tau_c))/(b-1))^(0.5))-1))
pi_c=linspace(5,30);


plot (pi_c,C_we,'k')
title('Figure 1. C_we vs. \pi_c');
xlabel('\pi_c')
ylabel('C_w_e')

Answer 1

[VBBV]

% Given
Ma=0.44
deltaH=17940;
W_cp=0.97;
P_a=12.93252;
m_dot=26;
T_t4=2150;
T_a=506.21;
gamma=1.4;
R=53.35;
Cp=0.2399565;
rho_8= 7.952636E-04;
% Diffuser
a_a=sqrt(gamma*R*32.17*T_a)
u_a=Ma*a_a
Tta_Ta=(1+0.5*(gamma-1).*Ma^2)
T_ta=506.21 * 1.03872
T_t2=T_ta
Pta_Pa=(Tta_Ta)^((gamma)/(gamma-1))
Pt2_Pa=Pta_Pa
P_t2=Pta_Pa*P_a
pi_c=linspace(5,30);
%Compressor
P_t3=pi_c.*P_t2
tau_c=pi_c.^((gamma-1)./gamma)
T_t3=tau_c*T_t2
%Primary Combustor
P_t4=P_t3
m_dotf=(m_dot*Cp*(T_t4-T_t3))./ deltaH
%Turbine
T_t5=(((m_dotf.*Cp.*(T_t3-T_t2)+W_cp*m_dotf*Cp*T_a)./(m_dotf*Cp))-T_t4)*-1
tau_t=T_t5./T_t4
pi_t= 0.2157084
P_t5=pi_t.*P_t4
%Primary Nozzle
T_t6=T_t5
P_t6=P_t5
P_8= 12.93252 %exit pressure matches ambient pressure
T_8=T_t6.*((P_8./P_t6).^((gamma-1)/gamma))
u_8=[2*Cp.*(T_t6-T_8)*32.17*778.16].^0.5
a_8=(gamma*R*T_8.*32.17).^0.5
M_8=u_8./a_8
A_8=m_dotf.*144./(rho_8.*u_8*32.17)
% Function for the work coefficient
tau_5=(T_ta./T_a).*tau_c.*tau_t;
a=T_t4./T_a
b=T_ta./T_a
c=T_a./T_ta
d=[((a*c.*((tau_t-1)./tau_c))./b-1).^(0.5)-1]
C_we=(a*(1-(tau_5./(b*tau_c)))-(b*(tau_c-1)))+((gamma-1).*(Ma.^2).*((((a*c.*((tau_5-1)./tau_c))./(b-1)).^(0.5))-1))
%%Graph
% 1. Cwe vs pi_c
f1=figure(1);clf;
C_we=(a.*(1-(tau_5./(b*tau_c)))-(b*(tau_c-1)))+((gamma-1)*(Ma.^2).*((((a*c.*((tau_5-1)./tau_c))./(b-1)).^(0.5))-1))
plot (pi_c,C_we,'k')
title('Figure 1. C_we vs. \pi_c');
xlabel('\pi_c')
ylabel('C_w_e')

[Marie Cor Cruz]

Thank you!