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| author | priyanka | 2015-06-24 15:03:17 +0530 |
|---|---|---|
| committer | priyanka | 2015-06-24 15:03:17 +0530 |
| commit | b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b (patch) | |
| tree | ab291cffc65280e58ac82470ba63fbcca7805165 /32/CH19/EX19.03/19_03.sce | |
| download | Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.tar.gz Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.tar.bz2 Scilab-TBC-Uploads-b1f5c3f8d6671b4331cef1dcebdf63b7a43a3a2b.zip | |
initial commit / add all books
Diffstat (limited to '32/CH19/EX19.03/19_03.sce')
| -rwxr-xr-x | 32/CH19/EX19.03/19_03.sce | 80 |
1 files changed, 80 insertions, 0 deletions
diff --git a/32/CH19/EX19.03/19_03.sce b/32/CH19/EX19.03/19_03.sce new file mode 100755 index 000000000..6f5294d3f --- /dev/null +++ b/32/CH19/EX19.03/19_03.sce @@ -0,0 +1,80 @@ +//pathname=get_absolute_file_path('19.03.sce')
+//filename=pathname+filesep()+'19.03-data.sci'
+//exec(filename)
+//Specific heat of gases(in kJ/kg.K):
+Cpg=1.14 //kJ/kg.K
+Cpa=1.005 //kJ/kg.K
+//Mechanical efficiency:
+nm=0.96
+//Polytropic efficiency of compressor:
+nc=0.87
+//Turbine efficiency:
+nt=0.90
+//Nozzle efficiency:
+nn=0.95
+//By pass ratio:
+B=5.5
+//Mass flow rate of air(in kg/s):
+ma=200
+//Pressures(in bar):
+p2=1.5
+p1=1
+p3=28
+pa=p1
+//Temperatures(in K):
+T1=288
+rg=1.33
+ra=1.4
+CV=43100 //kJ/kg
+T4=1573 //K
+//For compression:a1=((ne-1)/ne)
+a1=1/nc*(ra-1)/ra
+a1=0.328
+//For expansion:a2=(nt-1)/nt
+a2=nt*(rg-1)/rg
+a2=0.223
+//Temperature at state 2'(in K):
+T2a=T1*(p2/p1)^a1
+//Temperature at state 3'(in K):
+T3a=T2a*(p3/p2)^a2
+//Using nozzle efficiency:
+dT=nn*T2a*(1-(pa/p2)^((ra-1)/ra))
+//Velocity at exit of nozzle(in m/s):
+C8=sqrt(2*Cpa*10^3*dT)
+//Mass flow rate of bypass air(in kg/s):
+mab=ma*B/(B+1)
+//Mass flow rate of hot gases(in kg/s):
+mca=ma-mab
+//Thrust available due to by pass air(in kN):
+Tb=mab*C8/10^3
+//Air fuel ratio:
+r1=(Cpg*T4-Cpa*T3a)/(CV-Cpg*T4)
+//Temperature at state 5'(in K):
+T5a=T4-(Cpa*(T3a-T2a)/(nm*(1+r1)*Cpg))
+//Temperature at state 6'(in K):
+T6a=(Cpg*nm*T5a-(1+B)*Cpa*(T2a-T1))/(Cpg*nm)
+//Pressure at state 4(in bar):
+p4=p3-p2
+//Pressure at state 5(in bar):
+p5=p4*(T5a/T4)^(1/a2)
+//Pressure at state 6(in bar):
+p6=p5*(T6a/T5a)^(1/a2)
+//Critical pressure ratio:
+c=((rg+1)/2)^(rg/(rg-1))
+//Pressure at state 7(in bar):
+p7=p6/c
+//For exit nozzle(in K):
+dT1=nn*T6a*(1-(p7/p6)^((rg-1)/rg))
+//Velocity at exit of nozzle(in m/s):
+C7=sqrt(2*Cpg*10^3*dT1)
+//Thrust due to hot gases(in kN):
+Tg=mca*C7/10^3
+//Total thrust(in kN):
+Tt=Tg+Tb
+//Specific thrust(in kN/kg/s):
+st=Tt/ma
+printf("\n RESULT \n")
+printf("\nSpecific thrust = %f kN/kg/s",st)
+//Specific fuel consumption(in kg/h.N):
+sfc=r1*mca*3600/(Tt*10^3)
+printf("\nSpecific fuel consumption = %f kg/h.N",sfc)
\ No newline at end of file |