initial commit / add all books

1 files changed, 41 insertions, 0 deletions

diff --git a/3511/CH7/EX7.5/Ex7_5.sce b/3511/CH7/EX7.5/Ex7_5.sce
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+clc;

+pa=0.458; // Ambient pressure in bar

+Ta=248; // Ambient temperature in kelvin

+Ci=805*1000/3600; // Speed of the aircraft in m/s

+rp=4;// Pressure ratio

+DelP_comb=0.21; // Combustion chamber pressure loss in bar

+T03=1100; // Turbine inlet temperature in kelvin

+eff_ram=0.95; // Intake duct efficiency

+eff_c=0.85; // Compressor efficiency

+eff_T=0.90; // Turbine efficiency

+eff_m=0.99; // Mechanical efficiency of transmission

+eff_nozzle=0.95; // Nozzle efficiency

+CV=43; // Low calorific value in MJ/kg

+Ac=0.0935; // Nozzle outlet area in m^2

+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=287; // Characteristic gas constant in J/kg K

+

+p01=pa*(1+eff_ram*((1+Ci^2/(2*Cpa*Ta*10^3))^(r/(r-1))-1));

+p02=p01*rp;

+T01=Ta+Ci^2/(2*Cpa*10^3);

+T02=T01+T01*(rp^((r-1)/r)-1)/eff_c;

+T04=T03-(Cpa*(T02-T01))/(Cpg*eff_m);

+p03=p02-DelP_comb;

+T_04=T03-(T03-T04)/eff_T;

+p04=p03*(T_04/T03)^(r/(r-1));

+p04_pc=1/(1-(((rg-1)/(rg+1))/eff_nozzle))^(rg/(rg-1));

+Tc=T04*(1/p04_pc)^((rg-1)/rg);

+pc=p04/p04_pc;

+row_c=(pc*10^5)/(R*Tc);

+cj=sqrt (rg*R*Tc);

+m=row_c*Ac*cj;

+F=m*(cj-Ci)+Ac*(pc-pa)*10^5; // Total thrust

+mf=(m*Cpg*(T03-T02))/(CV*10^3);

+sfc=mf*3600/F; // specific fuel consumption

+

+disp ("N   (roundoff error)",F,"Total thrust = ");

+disp ("kg/N h   (roundoff error)",sfc,"specific fuel consumption = ");

+