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

---
 32/CH19/EX19.07/19_07.sce | 66 +++++++++++++++++++++++++++++++++++++++++++++++
 1 file changed, 66 insertions(+)
 create mode 100755 32/CH19/EX19.07/19_07.sce

(limited to '32/CH19/EX19.07/19_07.sce')

diff --git a/32/CH19/EX19.07/19_07.sce b/32/CH19/EX19.07/19_07.sce
new file mode 100755
index 000000000..c265cbcbc
--- /dev/null
+++ b/32/CH19/EX19.07/19_07.sce
@@ -0,0 +1,66 @@
+//pathname=get_absolute_file_path('19.07.sce')
+//filename=pathname+filesep()+'19.07-data.sci'
+//exec(filename)
+//Specific heat(in kJ/kg.K):
+Cpa=1.005
+Cpg=1.087
+ra=1.4
+rg=1.33
+//Gas constant(in kJ/kg.K):
+R=0.287
+//Speed of aeroplane(in m/s):
+C0=250
+//Velocity at exit of turbine(in m/s):
+C4a=180
+CV=43000 //kJ/kg
+//Thrust power(in kW):
+P=800
+//Temperatures(in K):
+T0=-20+273
+T2=474.25 
+T3=973
+//Pressures(in bar):
+p0=0.3
+p1=0.31
+p5=p0
+//Compressor efficiency:
+nc=0.85
+//Jet engine efficiency:
+nj=0.90
+//Pressure ratio:
+r1=6
+//Temperature at state 2(in K):
+T1=T0+C0^2/(2*Cpa*10^3)
+T2a=T1+(T2-T1)/nc
+//Pressure at state 2(in bar):
+p2=p1*r1
+p3=p2
+//Fuel air ratio:
+FA=(Cpa*T3-Cpg*T2a)/(CV-Cpa*T3)
+printf("\n RESULT \n")
+printf("\nAir-fuel ratio = %f:1",1/FA)
+//Temperature at state 4'(in K):
+T4a=T3-Cpa/Cpg*(T2a-T1)/(1+FA)
+//Temperature at state 4(in K):
+T4=T3-(T3-T4a)/nc
+//Pressure at state 4(in bar):
+p4=p3*(T4/T3)^(rg/(rg-1))
+//Temperature at state 5(in K):
+T5=T4a*(p5/p4)^((rg-1)/rg)
+//Nozzle exit velocity(in m/s):
+C5=sqrt(2*nj*(Cpg*10^3*(T4a-T5)+C4a^2/2))
+//Overall efficiency:
+no=(((1+FA)*C5-C0)*C0)/(FA*CV*10^3)*100
+//Rate of air consumption(in kg/s):
+ma=P*10^3/(((1+FA)*C5-C0)*C0)
+printf("\nRate of air consumption = %f kg/s",ma)
+//Power produced by the turbine(in kW):
+Pt=ma*(1+FA)*Cpg*(T3-T4a)
+printf("\nPower produced by turbine = %f kW",Pt)
+//Temperature at state 5'(in K):
+T5a=T4a-((C5^2-C4a^2)/(2*Cpg*10^3))
+//Density of exhaust gases(in m^3/kg):
+d5a=p5*10^2/(R*T5a)
+//Jet exit area(in m^2):
+Aj=ma*(1+FA)/(C5*d5a)
+printf("\nJet exit area = %f m^2",Aj)
\ No newline at end of file
-- 
cgit