initial commit / add all books

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 = ");