initial commit / add all books

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+clc

+clear

+

+//Input data

+Po=700 //Stagnation pressure in kPa

+To=500+273 //Stagnation temperature in K

+a1=3.5 //Ratio of exit area to throat area

+m=5.5 //Mass flow rate in kg/s

+Cp=1.005 //Specific heat capacity at constant pressure in kJ/kg-K

+k=1.4 //Adiabatic constant

+

+//Calculation

+My=1/sqrt(k) //Mach number downstream of shock

+M2=2.8 //Mach number at outlet from gas tables @a1 

+t1=0.389 //Static to Stagnation temperature ratio at exit from gas tables (M1,k=1.4,isentropic)

+T2=To*t1 //Exit temperature in K

+p1=0.0369 //Static to Stagnation pressure ratio at exit from gas tables (M1,k=1.4,isentropic)

+P2=Po*p1 //exit pressure in kPa

+p2=0.2  //Ratio of pressure at exit to pressure at critical state at exit from Rayleigh flow gas tables @M2

+Pt2=P2/p2 //Exit pressure at critical state in kPa

+t2=0.315 //Ratio of temperature at exit to temperature at critical state at exit from Rayleigh flow gas tables @M2

+Tt2=T2/t2 //Exit temperature at critical state in K

+t3=0.674 //Ratio of Stagnation temperature at exit to stagnation temperature at critical state at exit from Rayleigh flow gas tables @M2

+Tto2=To/t3 //Exit stagnation temperature at critical state in K

+Mx=1.2 //Mach number upstream of shock from gas tables @My

+p3=0.796 //Ratio of Static pressure before shock to critical pressure at exit from gas tables (Rayleigh flow,Mx,k=1.4)

+Px=Pt2*p3 //Static pressure before shock in kPa

+t4=0.912 //Ratio of Static temperature before shock to critical temperature at exit from gas tables (Rayleigh flow,Mx,k=1.4)

+Tx=Tt2*t4 //Static temperature before shock in K

+t5=0.978 //Ratio of Stagnation temperature before shock to critical Stagnation temperature at exit from gas tables (Rayleigh flow,Mx,k=1.4)

+Tox=Tto2*t5 //Stagnation temperature before shock in K

+p4=1.513 //Static pressure ratio after and before the shock from gas tables @Mx 

+Py=Px*p4 //Pressure after shock in kPa

+t6=1.128 //Temperature ratio after and before the shock from gas tables @Mx

+Ty=Tx*t6 //temperature after shock in K

+t7=0.875 //Ratio of Temperature after the shock to Stagnation temperature after shock from gas tables @Mx 

+Toy=Ty/t7 //Stagnation temperature after shock in K,

+p5=1.207 //Ratio of pressure after shock to pressure at critical state from gas tables @My

+Pt=Py/p5 //Critical pressure in kPa

+t8=1.028 //Ratio of temperature after shock to temperature at critical state from gas tables @My

+Tt=Ty/t8 //Critical temperature in K

+t9=0.978 //Ratio of Stagnation temperature after shock to Stagnation temperature at critical state from gas tables @My

+Tot=Toy/t9 //Stagnation temperature at critical state in K, calculation mistake in textbbok 

+q1=Cp*(Tox-To) //Amount of heat added in upstream of shock in kJ/s

+q2=Cp*(Tot-Toy) //Amount of heat added in downstream of shock in kJ/s

+Q=m*(q1+q2) //Amount of heat added in two pipe section in kJ/s

+

+//Output

+printf('(A)Amount of heat added in two pipe section is %3.2f kJ/s\n (B)Properties:\n Upstream of shock:\n    Pressure is %3.1f kPa\n    Temperature is %3.3f K\n    Stagnation temperature is %3.2f K\n    Mach number is %3.1f\n Downstream of shock:\n    Pressure is %3.3f kPa\n    Temperature is %3.3f K\n    Stagnation temperature is %3.1f K\n    Mach number is %3.3f\n At the throat:\n    Pressure is %3.2f kPa\n    Temperature is %3.3f K\n    Stagnation temperature is %3.2f K\n At the exit:\n    Pressure is %3.2f kPa\n    Temperature is %3.2f K\n    Mach number is %3.2f',Q,Px,Tx,Tox,Mx,Py,Ty,Toy,My,Pt,Tt,Tot,P2,T2,M2)