.//////   !        !"#!$#%&'$()*)+ , -.- q'qqq.' Turbojet analysis in SI units'Va 'm/s'Flight velocity'Altitude''m 'given'Ta03333@'K'Ambient temperature'PaC 'Bar'Ambient pressure 'Fuel HV\@ 'kJ/kg'Heating value 'Cpa  'kJ/kg'Air heat capacity 'Cpa/Cpg Z&? l?! 'Air-gas heat capacity ratio 'r  'Compressor pressure ratio 'm  'kg/s 'Inlet mass flow rate 'PR '  'Inlet pressure recovery 'comp eta % 'Compressor efficiency '(k-1)/k48EG?.'Compressor isentropic factor for k = 1.4'turb eta "'Turbine isentropic efficiecy'(kg-1)/kgU+'Turbine isentropic factor for k = 4/3'eta mechg 'mechanical efficiency'comb dp/p('Combustor fractional pressure loss 'To3=>'C"'Turbine inlet temperature, C 'To3= @"'K"'Turbine inlet temperature, K'To1=Toa=0Se@'K'Toa=Ta+Va^2/(2*Cpa*1000) 'Poa=(f?e 'Bar'Poa=Pa*(Toa/Ta)^[k/(k-1)] 'Po1=^>Ǐ?  'Bar%'Po1=Poa*inlet pressure recovery 'Po2=^>Ǐ@  'Bar'Po2=r*Po1 'Po3=!p@ 'Bar'Po3=Po2*[1 - (comb dp/p)] 'To2s=#߁@ 'K'To2s=To1*r^(k-1)/k 'To2=20Y_@ 'K#'To2=To1+(To2s-T01)/(comp eta) 'To4=2@ 'K*'To4=To3-(Cpa/Cpg)*(To2-To1)/eta mech 'To4s+2@'K#'To4s=To3-(To3-To4)/[turb eta] 'Po4=0(Iw@ 'Bar#'Po4=Po3*(To4/To3)^[kg/(kg-1)] 'Po4/PaF?xʃ@' Nozzle flow is1 chokednot choked; choked 'Po4/Pc0 x&$R?8v? 'Po4/Pc=[(k+1)/2]^[k/(k-1)] !'T5=N!p߫~@ xIc?;!'K.!'IFPc>Pa,To4*2/(4/3+1),To4/(Po4/Pa)^(1/4) "'V5=Y"0E@  ?>!#! #; "'m/s4"'IFPc>Pa,SQRT(287*T5*4/3),SQRT(2000(To4-T5)Cpg) #'P5=0# ?  ; #'Bar%#'IFPo4/Pa>Po4/Pc,Po4/(Po4/Pc),Pa $'rho5=%$(4諾?##! $'kg/m^3$'rho5=100*P5/(.287*T5) %'A5/m5=!%1?"$%'m^2-s/kg%'A5/m5=1/(C5*rho5)&'Spec.Thr@&86?"#%  &'kN-s/kg*&'[(V5-Va)+(P5-Pa)*(A5/m5)*10^5)]/1000 ''thrust'ʵW@ &''kN''Total engine thrust ('f/a=3(8:lʏ? ('f/a=Cpg(To3-To2)/HV)'mf)H? ( )'kg/s)'Fuel flow rate=m*(f/a) *'TSFC=*@4:P?(& *'kg/kN-s *'TSFC=(f/a)/specific thrust +'TSFC=+!hO@ *+'kg/kN-hr%+'TSFC=3600*(f/a)/specific thrust