1 files changed, 42 insertions, 0 deletions
diff --git a/3511/CH7/EX7.8/Ex7_8.sce b/3511/CH7/EX7.8/Ex7_8.sce
new file mode 100644
index 000000000..763c4c538
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+++ b/3511/CH7/EX7.8/Ex7_8.sce
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+clc;
+Ta=288; // Ambient temperature in kelvin
+pa=1.01; // Ambient pressure in bar
+p04=2.4; // Stagnation pressure in bar
+T04=1000;// Stagnation temperature in kelvin
+m=23; // Mass flow rate in kg/s
+rp=1.75; // Pressure ratio
+eff_f=0.88 ; // Efficiency of the fan
+eff_ft=0.9; // Efficiency of the fan turbine
+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
+T01=Ta;
+p01=pa;
+pc=p04*(2/(r+1))^(r/(r-1));
+// since pc>pa the nozzle will choke
+Tc=T04*(2/(r+1));
+row_c=pc*10^5/(R*Tc);
+cj=sqrt (r*R*Tc);
+A=m/(row_c*cj);
+p1=pa;
+F=m*cj+(A*(pc-p1)*10^5);
+// For fan engine
+T_02=T01*(rp)^((r-1)/r);
+T02=T01+(T_02-T01)/eff_f;
+// For cold nozzle
+m_nozzle=2*m; // Flow through cold nozzle
+pc1=p01*rp*(2/(r+1))^(r/(r-1));
+F_cold=m_nozzle*sqrt (2*Cpa*10^3*(T02-T01));
+// Fan Turbine
+T05=T04-((m_nozzle*Cpa*(T02-T01))/(m*Cpg));
+T_05=T04-(T04-T05)/eff_ft;
+p_05=p04*(T_05/T04)^(rg/(rg-1));
+pc=p_05*(2/(rg+1))^(rg/(rg-1));
+F_hot=m*sqrt (2*Cpg*10^3*(T05-T01));
+Takeoffthrust= F_cold + F_hot;
+
+disp ("m^2   (roundoff error)",A,"Nozzle Exit area = ");
+disp ("N   (roundoff error)",F,"Total Thrust = ");
+disp ("N   (roundoff error)",Takeoffthrust,"Take-off Thrust = ");