1 files changed, 47 insertions, 0 deletions
diff --git a/3511/CH7/EX7.9/Ex7_9.sce b/3511/CH7/EX7.9/Ex7_9.sce
new file mode 100644
index 000000000..44ac536d5
--- /dev/null
+++ b/3511/CH7/EX7.9/Ex7_9.sce
@@ -0,0 +1,47 @@
+clc;
+ma=18.2; // Massflow rater in m/s
+Mi=0.6; // Mach number 
+pa=0.55; // Ambient pressure in bar
+Ta=255; // Ambient temperature in kelvin
+rp=5; // Pressure ratio
+T03=1273; // Maximum temperature in kelvin
+eff_c=0.81; // Compressor efficiency
+eff_T=0.85; // Turbine efficiency
+eff_nozzle=0.915; // Nozzle efficiency
+eff_ram=0.9; // Intake duct efficiency
+CV=45870; // Low calorific value in kJ/kg
+Cpa=1.005;// Specific heat of air  at constant pressure in kJ/kg K
+Cpg=1.147;// Specific heat of fuel at constant pressure in kJ/kg K
+rg=1.33;// Specific heat ratio of fuel
+r=1.4; // Specific heat ratio of air
+R=284.6; // Characteristic gas constant in J/kg K
+
+ci=Mi*sqrt(r*R*Ta);
+T_01=Ta+ci^2/(2*Cpa*10^3);
+T01=T_01;
+p_01=pa*(T01/Ta)^(r/(r-01));
+p01=eff_ram*(p_01-pa)+pa;
+p02=rp*p01;
+T02=T01*(1+((rp^((r-1)/r))-1)/eff_c);
+Wc=ma*Cpa*(T02-T01);
+WT=Wc;
+mf=ma/((CV/(Cpg*(T03-T02)))-1);
+f1=mf/ma;
+T04=T03-(WT/((ma+mf)*Cpg));
+rp_T=(1/(1-((1-(T04/T03))/eff_T)))^(r/(r-1));
+p03=p02;
+p04=p03/rp_T;
+p04_pc=1/(1-((rg-1)/((rg+1)*eff_nozzle)))^(rg/(rg-1));
+pc=p04_pc/p04;
+Tc=T04*(1/p04_pc)^((rg-1)/rg);
+cj=sqrt (r*R*Tc);
+row_c=pc*10^5/(R*Tc);
+An=(ma+mf)/(row_c*cj);
+F=(ma+mf)*cj-ma*ci+An*(pc-pa);
+Fp=F*ci;
+
+disp ("kW   (roundoff error)",Wc,"Work of compression = ");
+disp ("kW   (roundoff error)",WT,"Power output of the turbine = ");
+disp (f1,"Fuel-Air ratio = ");
+disp ("N   (roundoff error)",F,"Thrust = ");
+disp ("kW   (roundoff error)",Fp/1000,"Thrust power = ");