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/CH4/EX4.4/4.sce | 33 +++++++++++++++++++++++++++++++++
 1 file changed, 33 insertions(+)
 create mode 100755 2126/CH4/EX4.4/4.sce

(limited to '2126/CH4/EX4.4')

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)
-- 
cgit