12222220  !         !"#$%&!'&()*$+,'-,. / 010 q'qqq:' Turbojet analysis with afterburner in SI units'Va 'm/s'Flight velocity'Altitude''m'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'turb eta #'Turbine isentropic efficiency'(kg-1)/kgU'Turbine isentropic factor'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$'Po4=Po3*(To4s/To3)^[kg/(kg-1)] 'delp&'fractional pressure loss - given 'Tob  'K# 'given afterburner temperature !'Pob!! 貸W@ !'Bar!'Pob=Po4(1-delp) "'Pob/Pa"g@!"' Nozzle flow is1"#"chokednot choked; "choked #'Pob/Pc0#x&$R?8v? #'Pob/Pc=[(k+1)/2]^[k/(k-1)] $'T5=N$,8I @"# xIc? ";$'K.$'IFP5>Pa,To4*2/(4/3+1),To4/(Po4/Pa)^(1/4) %'V5=Y%G4p{@"# ?>$# $ #; %'m/s4%'IFP5>Pa,SQRT(287*T5*4/3),SQRT(2000(To4-T5)Cpg) &'P5=0&U1?"#!#; &'Bar%&'IFPob/Pa>Pob/Pc,Pob/(Pob/Pc),Pa ''rho5=%'?&#$ ''kg/m^3''rho5=100*P5/(.287*T5) ('A5/m5=!( ?H?%'('m^2-s/kg('A5/m5=1/(C5*rho5))'Spec.Thr=@)НE1B?%&(  )'kN-s/kg*)'[(V5-Va)+(P5-Pa)*(A5/m5)*10^5)]/1000 *'thrust*HK~@ )*'kN*'Total engine thrust +'f/a=A+9D?  !+'f/a=Cpg(To3-To2+Tob-To4)/HV,'mf,hMNMu@ + ,'kg/s,'Fuel flow rate=m*(f/a) -'TSFC=-ؠW?+) -'kg/kN-s -'TSFC=(f/a)/specific thrust .'TSFC=.`Nk@ -.'kg/kN-hr%.'TSFC=3600*(f/a)/specific thrust