1 files changed, 33 insertions, 0 deletions
diff --git a/3511/CH7/EX7.7/Ex7_7.sce b/3511/CH7/EX7.7/Ex7_7.sce
new file mode 100644
index 000000000..40e2e1714
--- /dev/null
+++ b/3511/CH7/EX7.7/Ex7_7.sce
@@ -0,0 +1,33 @@
+clc;
+pa=0.7; // Ambient pressure in bar
+Ta=1+273; // Ambient temperature in kelvin
+Ci=800*1000/3600; // Speed of the aircraft in m/s
+rp=5;// Pressure ratio
+eff_ram=1.00; // Intake duct efficiency
+eff_c=0.85; // Compressor efficiency
+eff_T=0.90; // Turbine efficiency
+eff_comb=0.98; //Combustion efficiency 
+eff_nozzle=0.95; // Nozzle efficiency
+rp_T=2.23;// Turbine pressure ratio
+CV=43; // Low calorific value in MJ/kg
+Cpa=1.005;// Specific heat of air  at constant pressure in kJ/kg K
+Cpg=1.005;// Specific heat of fuel at constant pressure in kJ/kg K
+rg=1.4;// Specific heat ratio of fuel
+r=1.4; // Specific heat ratio of air
+R=287; // Characteristic gas constant in J/kg K
+F=25000; // Thrust in N
+
+cj=2*Ci;
+T_01=Ta+(Ci^2/(2*Cpa*10^3));
+T01=T_01;
+T02=T01+(T01*(((rp)^((r-1)/r))-1))/eff_c;
+p_01=pa*(1+Ci^2/(2*Cpa*10^3*Ta))^(r/(r-1));
+p01=eff_ram*(p_01-pa);
+p02=rp*p01;
+T03=(T02-T01)/(eff_T*(1-1/rp_T^((r-1)/r)));
+ma=F/(cj-Ci);
+// Neglecting the effect of the mass addition of fuel on the right hand side
+mf=(ma*Cpa*(T03-T02))/(eff_comb*CV*10^3);
+
+disp ("kg/s",ma,"Mass flow rate of air = ");
+disp ("kg/s   (roundoff error)",mf,"Mass flow rate of fuel = ");