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clc
t0 = 37 // Stangnation temperature in degree Celsius
P = 40 // Duct static pressure in kPa
g = 1.4 // Heat capacity ratio
function [x] = speed(a,b,f)
N = 100
eps = 1e-5;
if((f(a)*f(b))>0) then
error('no root possible f(a)*f(b)>0');
abort;
end;
if(abs(f(a))<eps) then
error('solution at a');
abort;
end
if(abs(f(b))<eps) then
error('solution at b');
abort;
end
while(N>0)
c = (a+b)/2
if(abs(f(c))<eps) then
x = c ;
x;
return;
end;
if((f(a)*f(c))<0 ) then
b = c ;
else
a = c ;
end
N = N-1;
end
error('no convergence');
abort;
endfunction
deff('[y]=p(x)',['y = x^4 + (5*(x^2)) - 3.225 '])
x = speed(0.5,1,p);
T0 = t0+273;
M = x; // Mach number
g = 1.4; // gamma
R = 0.287;
T = T0/(1+((g-1)/2)*M^2);
c = sqrt(g*R*T*1000);
V = c*M;
P0 = P*((T0/T)^(g/(g-1)));
printf("\n Example 17.1\n")
printf("\n Mach number is %f ",M)
printf("\n Velocity is %f m/s",V)
printf("\n Stagnation pressure is %f kPa",P0)
//The answers vary due to round off error
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