initial commit / add all books

1 files changed, 56 insertions, 0 deletions

diff --git a/2126/CH5/EX5.7/7.sce b/2126/CH5/EX5.7/7.sce
new file mode 100755
index 000000000..3ffd55e82
--- /dev/null
+++ b/2126/CH5/EX5.7/7.sce
@@ -0,0 +1,56 @@
+clc

+clear

+

+//Input data

+Po=800 //Pressure in reservoir in kPa

+To=40+273 //Temperature in reservoir in K

+M2a=2.5 //Mach number at exit from diagram

+At=25 //Throat Area in cm^2 

+Ax=40 //Area just before the shock in cm^2

+Ay=40 //Area just after the shock in cm^2

+k=1.4 //Adiabatic constant 

+R=287 //Specific gas constant in J/kg-K

+

+//Calculation

+t1=0.834 //Ratio of critical temperature and stagnation temperature from gas tables @M=1

+Tt=To*t1 //Critical temperature in K

+p1=0.528 //Ratio of critical pressure and stagnation pressure from gas tables @M=1

+Pt=Po*p1 //Critical pressure in kPa

+dt=Pt*10^3/(R*Tt) //Density in kg/m^3, Pt in Pa

+at=sqrt(k*R*Tt) //Velocity of sound at throat in m/s

+Ct=at //Air Velocity of sound at throat in m/s

+m=dt*At*10^-4*Ct //Mass flow rate in kg/s

+p2=0.0585 //Ratio of exit to stagnation pressure from isentropic gas tables @M2=2.5

+a1=2.637 //Ratio of exit to critical area from isentropic gas tables @M2=2.5

+A2=a1*At //Exit area in cm^2

+a2=Ax/At //Area ratio

+M=1.94 //Mach number upstream of shock from gas tables @a2

+p3=0.140 //Ratio of upstram of shock to stagnation pressures from isentropic gas tables @M

+Px=p3*Po //Pressure upstram of shock in kPa

+t2=0.570 //Ratio of upstram of shock to stagnation temperature from isentropic gas tables @M

+Tx=t2*To //Temperature upstram of shock in K

+My=0.588 //Mach number downstream of shock from normal shock gas tables @M

+p4=4.225 //Static pressure ratio after and before the shock from gas tables @My

+Py=Px*p4 //Static pressure after shock in kPa

+t3=1.639 //Temperature ratio after and before the shock from gas tables @My

+Ty=Tx*t3 //Temperature ratio after the shock in K

+p5=2.338 //Stagnation pressure after shock to Static pressure before shock from gas tables @My

+Poy=p5*Px //Stagnation pressure after shock in kPa

+p6=0.749 //Stagnation pressure ratio after and before the shock from gas tables @My

+Pox=Poy/p6 //Stagnation pressure before shock in kPa 

+//Here At2=Aty, Po2=Poy, Toy=To2=To1=To

+p7=0.79 //Static to stagnation pressure ratio after shock from isentropic gas tables @My

+Po2=Py/p7 //Stagnation pressure at exit in kPa

+t4=0.935 //Static to stagnation temperature ratio after shock from isentropic gas tables @My

+To2=Ty/t4 //Stagnation temperature in K (checked)

+a3=1.2 //Ratio of areas after shock i.e. (Ay/At2)

+At2=Ay/a3 //Critical area after shock in cm^2

+a4=A2/At2 //Ratio of areas 

+M2b=0.31 //Mach number at exit from gas tables @a4(as per section-b)

+p8=0.936 //Static to stagnation pressure ratio at exit from isentropic gas tables @M2b

+P2=Po2*p8 //Exit pressure in kPa

+t5=0.981 //Static to stagnation temperature ratio after shock from isentropic gas tables @M2b

+T2=To2*t5 //Exit temperature in K

+

+//Output

+printf('CASE-I:\n    (A)Mass flow rate is %3.2f kg/s\n    (B)Exit area is %3.1f cm^2\n CASE-II:\n    (A)Temperature is %3.3f K\n    (B)Pressure is %3.1f kPa',m,A2,T2,P2)