1 files changed, 51 insertions, 0 deletions
diff --git a/32/CH19/EX19.06/19_06.sce b/32/CH19/EX19.06/19_06.sce
new file mode 100755
index 000000000..a60b3a6ca
--- /dev/null
+++ b/32/CH19/EX19.06/19_06.sce
@@ -0,0 +1,51 @@
+//pathname=get_absolute_file_path('19.06.sce')
+//filename=pathname+filesep()+'19.06-data.sci'
+//exec(filename)
+//Calorific value(in kJ/kg):
+CV=45000
+//Inlet temperature(in C):
+T1=1000
+T4=T1
+//Nozzle efficiency:
+nn=0.9
+//Diffuser efficiency:
+nd=0.9
+//Compressive efficiency:
+nc=0.8
+//Turbine efficiency:
+nt=0.8
+//Specific heat(in kJ/kg.K):
+Cp=1.005
+p3=7.248 //bar
+p4=p3-0.15
+r=1.4
+p6=0.7
+//Gas constant(in kJ/kg.K):
+R=0.287
+//Temperature at state 2(in K):
+T2a=282.11
+T3a=568.635
+//Air fuel ratio:
+r1=(CV-T1*Cp)/(Cp*T1-Cp*T3a)
+//Temperature at state 5'(in K):
+T5a=T4-(T3a-T2a)
+//Temperature at state 5(in K):
+T5=T4-(T4-T5a)/nt
+p5=p4*(T5/T4)^(r/(r-1))
+//Temperature at state 6(in K):
+T6=T5a*(p6/p5)^((r-1)/r)
+//Temperature at state 6'(in K):
+T6a=T5a-(T5a-T6)*nn
+//Velocity at exit of nozzle(in m/s):
+C6=sqrt(2*Cp*(T5a-T6a)*10^3)
+//Volume flow rate of air(in m^3/s):
+v=200/10
+//Mass flow rate(in kg/s):
+m=0.7*10^2*v/(R*260)
+//Specific thrust(in N/kg of air/s):
+St=(1+1/r1)*C6
+printf("\n RESULT \n")
+printf("\nSpecific thrust = %f N/kg of air/s",St)
+//Total thrust(in N):
+Tt=m*St
+printf("\nTotal thrust = %f N",Tt)
+\ No newline at end of file