initial commit / add all books

1 files changed, 33 insertions, 0 deletions

diff --git a/2126/CH4/EX4.4/4.sce b/2126/CH4/EX4.4/4.sce
new file mode 100755
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+++ b/2126/CH4/EX4.4/4.sce
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+clc

+clear

+

+//input data

+C1=100 //Air velocity into combustion chamber in m/s

+P1=3 //Static Pressure at entry in bar

+T1=318 //Static Temperature at entry in K

+q=630 //The heat transferred per unit mass flow in kJ/kg

+Cp=1.005 //Specific heat of dry air in kJ/kg-K

+k=1.4 //Adiabatic constant

+R=287 //Gas constant in J/kg-K

+

+//calculation

+a1=sqrt(k*R*T1) //Sound velocity in m/s

+M1=C1/a1 //Mach number at entry

+t1=0.985 //Temperature ratio at entry from gas tables (M1,k=1.4,isentropic)

+To1=T1/t1 //Total stagnation temperature at inlet in K

+p1=0.947 //Pressure ratio  at entry from gas tables (M1,k=1.4,isentropic)

+Po1=P1/p1 //Stagnation Pressure at entry in bar

+To2=(q/Cp)+To1 //Stagnation exit temperation in K

+p2=2.163 //Static Pressure ratio  at critical state from gas tables (Rayleigh,k=1.4,M=0.28)

+Pt=P1/p2 //Static critical pressure in bar 

+p3=2.206 //Stagnation Pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.28)

+Pot=Po1/p3 //Stagnation critical pressure in bar

+t2=0.310 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.28)

+Tot=To1/t2 //Stagnation critical temperature in K

+t3=(To2/Tot) //Stagnation Temperature ratio at exit

+M2=0.7 //Mack number at exit from gas tables (Rayleigh,t3)

+p4=1.423 //Static Pressure ratio  at exit from gas tables (Rayleigh,t3,M2)

+P2=p4*Pt //Static Pressure at exit in bar

+

+//output 

+printf('(A)Pressure after combustion is %3.3f bar\n (B)Mach number after combustion is %3.1f',P2,M2)