From b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b Mon Sep 17 00:00:00 2001
From: priyanka
Date: Wed, 24 Jun 2015 15:03:17 +0530
Subject: initial commit / add all books

---
 2126/CH5/EX5.24/24.sce | 49 +++++++++++++++++++++++++++++++++++++++++++++++++
 1 file changed, 49 insertions(+)
 create mode 100755 2126/CH5/EX5.24/24.sce

(limited to '2126/CH5/EX5.24/24.sce')

diff --git a/2126/CH5/EX5.24/24.sce b/2126/CH5/EX5.24/24.sce
new file mode 100755
index 000000000..69a5ecdb1
--- /dev/null
+++ b/2126/CH5/EX5.24/24.sce
@@ -0,0 +1,49 @@
+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)
-- 
cgit