initial commit / add all books

14 files changed, 423 insertions, 0 deletions

diff --git a/2126/CH4/EX4.1/1.sce b/2126/CH4/EX4.1/1.sce
new file mode 100755
index 000000000..b7bc42199
--- /dev/null
+++ b/2126/CH4/EX4.1/1.sce
@@ -0,0 +1,22 @@
+clc

+clear

+

+//input data

+Pa=1*10^5 //Pressure of dry air in Pa

+To1=288 //Total stagnation temperature at inlet in K

+M1=1 //Mach number at inlet of pipe

+M2=0.8 //Mach number at exit o pipe

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

+ 

+//calculation

+t1=0.834 //Temperature ratio at entry, i.e.entry static temperature to total temperature from gas tables at isentropic,M1=1 & adiabatic constant=1.4

+T1=t1*To1 //Static temperature at entry in Kelvin

+t2=0.964 //Temperature ratio at critical state, i.e. exit stagnation temperature to critical state temperature from gas tables at Rayleigh, M2=0.8 & adiabatic constant=1.4

+To2=t2*To1 //Total stagnation temperature at exit in K

+t3=1.025 //Temperature ratio at exit, i.e. exit static temperature to total temperature from gas tables at isentropic,M1=1 & adiabatic constant=1.4

+T2=t3*T1 //Static temperature at exit in Kelvin

+q=Cp*(To1-To2) //The heat transferred per unit mass flow in kJ/kg

+dT=To1-T2 //Change in temperature in K

+

+//output

+printf('(A)The heat transferred per unit mass flow is %3.3f kJ/kg (rejected)\n (B)Change in temperature is %3.3f K',q,dT)

diff --git a/2126/CH4/EX4.10/10.sce b/2126/CH4/EX4.10/10.sce
new file mode 100755
index 000000000..0befb323e
--- /dev/null
+++ b/2126/CH4/EX4.10/10.sce
@@ -0,0 +1,43 @@
+clc

+clear

+

+//input data

+T1=560 //Static Temperature at entry in K

+P1=0.6 //Static Pressure at entry in bar

+C1=75 //Air velocity into combustion chamber in m/s

+mp=30 //air fuel ratio

+CV=92000 //Calorific value of fuel 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=0.9949 //Temperature ratio at entry from gas tables (M1,k=1.4,isentropic)

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

+p1=0.982 //Pressure ratio  at entry from gas tables (M1,k=1.4,isentropic)

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

+q=CV/(mp+1) //The heat transferred per unit mass flow in kJ/kg of gas, mp+1=total amount of fuel=mf+ma

+p2=2.317 //Static Pressure ratio  at critical state from gas tables (Rayleigh,k=1.4,M1)

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

+p3=1.246 //Stagnation Pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

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

+t2=0.137 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M1) 

+Tt=T1/t2 //Static critical temperature in K

+t3=0.115 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

+Tot=To1/t3 //Stagnation critical temperature in K

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

+t4=To2/Tot //Ratio of stagnation temperature at exit and critical state 

+M2=0.33 //Mach number at exit from gas tables (Rayleigh,t4,k=1.4)

+p4=2.0825 //Static Pressure ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

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

+p5=1.186 //Stagnation Pressure ratio at exit from gas tables (Rayleigh,t4,k=1.4)

+Po2=Pot*p5 //Stagnation Pressure at exit in bar

+t5=0.472 //Static temperature ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+T2=t5*Tt //Static exit temperature in K

+C2=M2*sqrt(k*R*T2) //exit velocity in m/s

+SPL=((Po1-Po2)/Po1)*100 //Percentage of pressure loss in combustion chamber in %

+

+//output

+printf('(A)At exit:\n    Pressure is %3.5f bar \n    Temperature is %3i K \n    Velocity is %3.2f m/s \n    Mach number is %3.2f \n (B)Maximum stagnation temperature available is %3.2f K\n (C)Percentage of pressure loss in combustion chamber is %3.1f percent\n (D)Intial Mach number is %3.2f \n',P2,T2,C2,M2,Tot,SPL,M1)

diff --git a/2126/CH4/EX4.11/11.sce b/2126/CH4/EX4.11/11.sce
new file mode 100755
index 000000000..46a79b548
--- /dev/null
+++ b/2126/CH4/EX4.11/11.sce
@@ -0,0 +1,19 @@
+clc

+clear

+

+//input data

+To1=473 //Total stagnation temperature at inlet in K

+To2=673 //Stagnation exit temperation in K

+M1=0.5 //Mach number at entry

+

+//calculation

+t1=0.6914 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

+p1=1.7778 //Static pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

+t2=(To2/To1)*t1 //Stagnation temperature ratio at exit 

+M2=0.867 //Mach number at exit from gas tables (Rayleigh,t2,k=1.4)

+p2=1.16 //Static pressure ratio at exit from gas tables (Rayleigh,k=1.4,M2)

+p=p2/p1 //ratio of static pressures at oulet and inlet

+PL=(1-p)*100 //pressure loss in %

+

+//output

+printf('(A)Mach number is %3.3f\n (B)Percentage drop in pressure is %3.1f percent',M2,PL) 

diff --git a/2126/CH4/EX4.12/12.sce b/2126/CH4/EX4.12/12.sce
new file mode 100755
index 000000000..8c15f5859
--- /dev/null
+++ b/2126/CH4/EX4.12/12.sce
@@ -0,0 +1,18 @@
+clc

+clear

+

+//input data

+t1=3 //Stagnation temperature ratio

+M2=0.8 //Mach number at exit

+

+//calculation

+t2=0.964 //Ratio of stagnation temperature at exit and critical state (Rayleigh,M2,k=1.4) 

+p1=1.266 //Static Pressure ratio  at exit from gas tables (Rayleigh,M2,k=1.4)

+t3=t2/t1 //Stagnation temperature ratio at critical state 

+M1=0.29 //Mach number at entry from gas tables (Rayleigh,t3,k=1.4)

+p2=2.147 //Static pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

+p=p1/p2 //ratio of static pressures at exit and entry

+PL=(1-p)*100 //Percentage loss in static pressure in %

+

+//output

+printf('(A)Mach number at entry is %3.2f\n (B)Percentage loss in static pressure is %3i percent',M1,PL)

diff --git a/2126/CH4/EX4.13/13.sce b/2126/CH4/EX4.13/13.sce
new file mode 100755
index 000000000..c8c2bb99c
--- /dev/null
+++ b/2126/CH4/EX4.13/13.sce
@@ -0,0 +1,22 @@
+clc

+clear

+

+//input data

+To1=300 //Total stagnation temperature at inlet in K

+To2=310 //Stagnation exit temperation in K

+G=1300 //Mass velocity in kg/m^2-s

+P1=105*10^3 //Static Pressure at entry in Pa

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

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

+

+//calculation

+T1=(((-2*P1^2*Cp)+sqrt(((-2*P1^2*Cp)^2)+(8*G^2*R^2*P1^2*Cp*To1)))/(2*G^2*R^2)) //Static temperature in K

+t1=T1/To1 //Temperature ratio at entry

+M1=1.4 //Mach number at entry from gas tables (isentropic,t1,k=1.4)

+t2=0.934 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M1)

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

+t3=To2/Tot //Stagnation temperature ratio at exit from gas tables (Rayleigh,k=1.4,M1)

+M2=1.26 //Mach number at exit from gas tables (Rayleigh,t3,k=1.4)

+

+//output 

+printf('(A)The inlet mach number is %3.2f \n (B)The exit mach number is %3.2f',M1,M2)

diff --git a/2126/CH4/EX4.14/14.sce b/2126/CH4/EX4.14/14.sce
new file mode 100755
index 000000000..2d4255664
--- /dev/null
+++ b/2126/CH4/EX4.14/14.sce
@@ -0,0 +1,38 @@
+clc

+clear

+

+//input data

+k=1.3 //Adiabatic constant

+R=466 //Gas constant in J/kg-K

+P1=0.345 //Static Pressure at entry in Pa

+T1=312 //Static Temperature at entry in K

+C1=65.5 //Entry velocity in m/s

+q=4592 //The heat transferred per unit mass flow in kJ/kg

+

+//calculation

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

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

+t1=0.9965 //Temperature ratio at entry from gas tables (M1,k=1.3,isentropic)

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

+p1=2.235 //Static Pressure ratio  at critical state from gas tables (Rayleigh,k=1.3,M1)

+Pt=P1/p1 //Static critical pressure in bar 

+c1=0.051 //Velocity ratio at critical state from gas tables (Rayleigh,k=1.3,M1)

+Ct=C1/c1 //Critical velocity in m/s

+t2=0.112 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.3,M1) 

+Tt=T1/t2 //Static critical temperature in K

+t3=0.098 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.3,M1)

+Tot=To1/t3 //Stagnation critical temperature in K

+Cp=(k*R)/(k-1) //Specific heat of dry air in kJ/kg-K

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

+t4=(To2/Tot) //Stagnation Temperature ratio at exit

+M2=0.60 //Mack number at exit from gas tables (Rayleigh,t4)

+p2=1.567 //Static Pressure ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+P2=p2*Pt //Static Pressure at exit in bar 

+t5=0.884 //Static temperature ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+T2=t5*Tt //Static exit temperature in K

+c2=0.564 //Velocity ratio at critical state from gas tables (Rayleigh,k=1.4,t4)

+C2=Ct*c2 //exit velocity in m/s

+qmax=Cp*(Tot-To1)/10^3 //Maximum possible heat transfer in kJ/kg 

+

+//output

+printf('(A)Heat required to accelerate the gas from the inlet condition to sonic condition is %3.2f kJ/kg\n (B)The pressure and temperature at sonic condition are %3.3f bar and %3.2f K respectively\n (C)The properties at exit are:\n    Pressure is %3.3f bar\n    Temperature is %3.2f K\n    Velocity is %3i m/s',qmax,Pt,Tt,P2,T2,C2)

diff --git a/2126/CH4/EX4.2/2.sce b/2126/CH4/EX4.2/2.sce
new file mode 100755
index 000000000..702856993
--- /dev/null
+++ b/2126/CH4/EX4.2/2.sce
@@ -0,0 +1,37 @@
+clc

+clear

+

+//input data

+M1=3 //Mach number at entry

+P1=1 //Static Pressure at entry in atm

+T1=300 //Static Temperature at entry in K

+q=300 //The heat transferred per unit mass flow in kJ/kg

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

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

+

+//calculation

+t1=2.8 //Temperature ratio at entry from gas tables (M=3,k=1.4,isentropic)

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

+p1=0.0272 //Pressure ratio  at entry from gas tables (M=3,k=1.4,isentropic)

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

+p2=0.176 //Static Pressure ratio  at critical state from gas tables (Rayleigh,k=1.4,M=3)

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

+p3=3.424 //Stagnation Pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=3)

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

+t2=0.281 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=3) 

+Tt=T1/t2 //Static critical temperature in K

+t3=0.654 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=3)

+Tot=To1/t3 //Stagnation critical temperature in K

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

+t4=(To2/Tot) //Stagnation Temperature ratio at exit

+M2=1.6 //Mack number at exit from gas tables (Rayleigh,t4)

+p4=0.524 //Static Pressure ratio  at exit from gas tables (Rayleigh,t4=0.866,M=1.6)

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

+p5=1.176 //Stagnation Pressure ratio at exit from gas tables (Rayleigh,t4=0.866,M=1.6)

+Po2=p5*Pot //Stagnation Pressure at exit in atm

+t5=0.702 //Static temperature ratio at exit from gas tables (Rayleigh,t4=0.866,M=1.6)

+T2=t5*Tt //Static exit temperature in K

+d2=P2*101325/(R*T2) //density of air at exit in kg/m^3, P2 in N/m^2

+

+//outpur

+printf('(A)The Mach numer at exit is %3.1f\n (B)Static Pressure at exit is %3.3f atm\n (C)Static exit temperature is %3.2f K\n (D)density of air at exit is %3.4f kg/m^3\n (E)Stagnation exit temperation is %3.2f K\n (F)Stagnation Pressure at exit is %3.2f atm',M2,P2,T2,d2,To2,Po2)

diff --git a/2126/CH4/EX4.3/3.sce b/2126/CH4/EX4.3/3.sce
new file mode 100755
index 000000000..f1b60af65
--- /dev/null
+++ b/2126/CH4/EX4.3/3.sce
@@ -0,0 +1,29 @@
+clc

+clear

+

+//input data

+M1=2 //Mach number at entry

+P1=1.4 //Static Pressure at entry in bar

+T1=323 //Static Temperature at entry in K

+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

+t1=0.555 //Temperature ratio at entry from gas tables (M=2,k=1.4,isentropic)

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

+p1=0.364 //Pressure ratio  at entry from gas tables (M=2,k=1.4,isentropic)

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

+t2=0.529 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2) 

+Tt=T1/t2 //Static critical temperature in K

+t3=0.793 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2)

+Tot=To1/t3 //Stagnation critical temperature in K

+To2=Tot //Stagnation exit temperation in K

+q=Cp*(To2-To1) //The heat transferred per unit mass flow in kJ/kg

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

+C1=M1*a1 //Air velocity in m/s

+d1=(P1*10^5)/(R*T1) //density of air in kg/m^3

+ma=d1*C1 //Mass flow rate per unit area in kg/s-m^3

+

+//output

+printf('(A)Mass flow rate per unit area is %3.2f kg/s-m^2\n (B)Final temperarure is %3.3f K\n (C)Heat added is %3.2f kJ/kg',ma,Tt,q)

diff --git a/2126/CH4/EX4.4/4.sce b/2126/CH4/EX4.4/4.sce
new file mode 100755
index 000000000..aa221ed5a
--- /dev/null
+++ b/2126/CH4/EX4.4/4.sce
@@ -0,0 +1,33 @@
+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)

diff --git a/2126/CH4/EX4.5/5.sce b/2126/CH4/EX4.5/5.sce
new file mode 100755
index 000000000..f137edca4
--- /dev/null
+++ b/2126/CH4/EX4.5/5.sce
@@ -0,0 +1,40 @@
+clc 

+clear

+

+//input data

+M1=3 //Mach number at entry

+To1=295 //Total stagnation temperature at inlet in K

+P1=0.5 //Static Pressure at entry in bar

+M2=1.5 //Mack number at exit

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

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

+

+//calculation

+p1=0.0272 //Pressure ratio  at entry from gas tables (M=3,k=1.4,isentropic)

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

+t1=0.357 //Temperature ratio at entry from gas tables (M=3,k=1.4,isentropic)

+T1=t1*To1 //Static temperature at entry in Kelvin

+p2=0.176 //Static Pressure ratio  at critical state from gas tables (Rayleigh,k=1.4,M=3)

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

+p3=3.424 //Stagnation Pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=3)

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

+t2=0.654 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=3)

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

+t3=0.280 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=3)

+Tt=T1/t3 //Static critical temperature in K

+p4=0.578 ////Static Pressure ratio  at exit from gas tables (Rayleigh,M=1.5)

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

+p5=1.122 //Stagnation Pressure ratio at exit from gas tables (Rayleigh,M=1.5)

+Po2=p5*Pot //Stagnation Pressure at exit in bar

+t4=0.753 ////Static temperature ratio at exit from gas tables (Rayleigh,M=1.5)

+T2=t4*Tt //Static exit temperature in K

+t5=0.909 //Stagnation temperature ratio at exit from gas tables (Rayleigh,M=1.5)

+To2=t5*Tot //Total stagnation temperature at exit in K

+q=Cp*(To1-To2) //The heat transferred per unit mass flow in kJ/kg

+SPC=Po1-Po2 //Change in stagnation pressure in bar

+n=log(Po1/Po2)/(log(Po1/Po2)-log(To1/To2)) //Exponent of polytropic equation

+qmax=Cp*(Tot-To1) //Maximum possible heat transfer in kJ/kg

+ds=Cp*log(T2/T1)-(R*log(P2/P1)) //Change in entropy in kJ/kg-K

+

+//output

+printf('(A)Total temperature at exit is %3.2f K\n (B)Static pressure at exit is %3.3f bar \n (C)Change in stagnation pressure is %3.2f bar\n (D)Exponent of polytropic equation is %3.2f',To2,P2,SPC,n)

diff --git a/2126/CH4/EX4.6/6.sce b/2126/CH4/EX4.6/6.sce
new file mode 100755
index 000000000..640178b23
--- /dev/null
+++ b/2126/CH4/EX4.6/6.sce
@@ -0,0 +1,32 @@
+clc

+clear

+

+//input data

+M2=0.9 //Mack number at exit

+P2=2.5 //Static Pressure at exit in bar

+T2=1273 //Static exit temperature in K

+t1=3.74 //ratio of stagnation temperatures at and exit entry

+Cp=1.218 //Specific heat of dry air in kJ/kg-K

+k=1.3 //Adiabatic constant

+

+//calculation

+t2=0.892 //Temperauture ratio at exit from gas tables (isentropic,k=1.3,M=0.9)

+To2=T2/t2 //Total stagnation temperature at exit in K

+To1=To2/t1 //Total stagnation temperature at inlet in K

+p1=1.12 //Static pressure ratio at critical state from gas tables (Rayleigh,k=1.3,M=1.5)

+Pt=P2/p1 //Static critical pressure in bar

+t3=1.017 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.3,M=1.5)

+Tt=T2/t3 //Static critical temperature in K

+t4=0.991 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.3,M=1.5)

+Tot=To2/t4 //Stagnation critical temperature in K

+t5=To1/Tot //Ratio of stagnation temperature at entry and critical state  

+M1=0.26 //Mach number at entry from gas tables (Rayleigh,t5,k=1.3)

+p2=2.114 //Static Pressure ratio  at entry from gas tables (Rayleigh,t5,k=1.3)

+P1=Pt*p2 //Static Pressure at entry in bar

+t6=0.302 //Static temperature ratio  at entry from gas tables (Rayleigh,t5,k=1.3)

+T1=Tt*t6 //Static temperature at entry in Kelvin

+q=Cp*(To2-To1) //The heat transferred per unit mass flow in kJ/kg

+qmax=Cp*(Tot-To1) //Maximum possible heat transfer in kJ/kg 

+

+//output

+printf('(A)Mach number at entry is %3.2f\n (B)Pressure at entry is %3.3f bar \n (C)Temperature of gas is %3i K\n (D)Amount of heat added is %3.2f kJ/kg\n (E)Maximum heat that can be heated is %3.3f kJ/kg',M1,P1,T1,q,qmax)

diff --git a/2126/CH4/EX4.7/7.sce b/2126/CH4/EX4.7/7.sce
new file mode 100755
index 000000000..ccdb2332a
--- /dev/null
+++ b/2126/CH4/EX4.7/7.sce
@@ -0,0 +1,37 @@
+clc

+clear

+

+//input

+P1=0.343 //Static Pressure at entry in bar

+T1=310 //Static temperature at entry in Kelvin

+C1=60 //Velocity at entrance in m/s

+q=1172.5 //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=0.9943 //Temperature ratio at entry from gas tables (M=0.17,k=1.4,isentropic)

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

+p1=2.306 //Static Pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.17)

+Pt=P1/p1 //Static critical pressure in bar

+t2=0.154 //Static temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.17) 

+Tt=T1/t2 //Static critical temperature in K

+t3=0.129 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.17)

+Tot=To1/t3 //Stagnation critical temperature in K

+c1=0.0665 //Velocity ratio at critical state from gas tables (Rayleigh,k=1.4,M=0.17)

+Ct=C1/c1 //Critical velocity in m/s

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

+t4=To2/Tot //Ratio of stagnation temperature at exit and critical state 

+M2=0.45 //Mach number at exit from gas tables (Rayleigh,t4,k=1.4)

+p2=1.87 //Static Pressure ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+P2=p2*Pt //Static Pressure at exit in bar 

+t5=0.7075 //Static temperature ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+T2=t5*Tt //Static exit temperature in K

+c2=0.378 //Velocity ratio at critical state from gas tables (Rayleigh,k=1.4,t4)

+C2=Ct*c2 //exit velocity in m/s

+

+//output

+printf('At exit conditions :\n (A)Mach number is %3.2f\n (B)Pressure is %3.3f bar\n (C)Temperature is %3.2f K\n (D)Exit velocity is %3.2f m/s',M2,P2,T2,C2)

diff --git a/2126/CH4/EX4.8/8.sce b/2126/CH4/EX4.8/8.sce
new file mode 100755
index 000000000..0e4b2edab
--- /dev/null
+++ b/2126/CH4/EX4.8/8.sce
@@ -0,0 +1,27 @@
+clc

+clear

+

+//input data

+M1=2 //Mach number at entry

+To1=523 //Total stagnation temperature at inlet in K

+Po1=6 //Stagnation Pressure at entry in bar

+To2=423 //Stagnation exit temperation in K

+

+//calculation

+t1=0.555 //Temperature ratio at entry from gas tables (M=2,k=1.4,isentropic)

+T1=t1*To1 //Static temperature at entry in Kelvin

+p1=0.128 //Pressure ratio  at entry from gas tables (M=2,k=1.4,isentropic)

+P1=Po1*p1 //Static Pressure at entry in bar

+p2=0.364 //Static pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=2)

+p3=1.503 ////Stagnation pressure ratio at critical state from gas tables (Rayleigh,k=1.4,M=2), printing mistake in textbook

+t2=0.529 //Static Temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2)

+t3=0.793 //Stagnation temperature ratio at critical state from gas tables (Rayleigh,k=1.4,M=2)

+t4=(To2/To1)*t3 //Ratio of stagnation temperature at exit and critical state 

+M2=3.15 //Mach number at exit from gas tables (Rayleigh,t4,k=1.4)

+p4=0.161 //Static Pressure ratio  at exit from gas tables (Rayleigh,t4,k=1.4), printing mistake in textbook

+t5=0.258 //Static temperature ratio  at exit from gas tables (Rayleigh,t4,k=1.4)

+P2=(p4/p2)*P1 //Static Pressure at exit in bar 

+T2=(t5/t2)*T1 //Static exit temperature in K

+

+//output

+printf('After Cooling :\n (A)Mach number is %3.2f\n (B)Pressure is %3.4f bar\n (C)Temperature is %3.2f K',M2,P2,T2)

diff --git a/2126/CH4/EX4.9/9.sce b/2126/CH4/EX4.9/9.sce
new file mode 100755
index 000000000..70db49ba4
--- /dev/null
+++ b/2126/CH4/EX4.9/9.sce
@@ -0,0 +1,26 @@
+clc

+clear

+

+//input data

+M2=0.8 //Mack number at exit

+t1=4 //Ratio of stagnation temperature at exit and entry

+T1=288 //Atmospheric temperature in K

+P1=1 //Atmospheric Pressure in atm

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

+

+//calculation

+t2=0.964 //Ratio of stagnation temperature at exit and critical state from gas tables

+t3=t2/t1 //Ratio of stagnation temperature at entry and critical state

+M1=0.24 ////Mach number at entry from gas tables (Rayleigh,t3,k=1.4)

+t5=0.988 //Temperature ratio at entry from gas tables (M1,k=1.4,isentropic)

+To1=T1/t5 //Total stagnation temperature at inlet in K

+To2=t1*To1 //Stagnation exit temperation in K

+Tot=To1/t3 //Stagnation critical temperature in K

+q=Cp*(To2-To1) //The heat transferred per unit mass flow in kJ/kg

+qmax=Cp*(Tot-To1) //Maximum possible heat transfer in kJ/kg 

+t6=0.9775 //Ratio of stagnation temperature for maximum static temperature (M=1/sqrt(k),Rayleigh)

+To3=Tot*t6 //maximum stagnation temperature in K

+q_req=Cp*(To3-To1) //Heat transfer required to get maximum static temperature in kJ/kg

+

+//output

+printf('(A)Heat added per kg of air flow is %3.2f kJ/kg\n (B)Maximum possible heat transfer is %3.2f kJ/kg\n (C)Heat transfer required to get maximum static temperature is %3.1f kJ/kg',q,qmax,q_req)