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//All the quantities are expressed in SI units
u1 = 680; //velocity upstream of shock
T1 = 288; //temperature upstream of shock
p1 = 1; //pressure upstream of shock
gam = 1.4; //ratio of specific heats
R = 287; //universal gas constant
//the speed of sound is given by
a1 = sqrt(gam*R*T1)
//thus the mach number is
M1 = 2;
//from Appendix B, for M = 2, the relations between pressure and temperature are given by
pressure_ratio = 4.5; //ratio of pressure accross shock
temperature_ratio = 1.687; //ratio of temperature accross shock
M2 = 0.5774; //mach number downstream of shock
//thus the values downstream of the shock can be calculated as
p2 = pressure_ratio*p1;
T2 = temperature_ratio*T1;
a2 = sqrt(gam*R*T2);
u2 = M2*a2;
printf("\nRESULTS\n---------\n p2 = %1.1f atm\n T2 = %3.0f K\n u2 = %3.0f m/s",p2,T2,u2)
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