=>>>>>>> !       ! "#$"%#&'( )*!+*,-&.'/( 0121324567839:8;4< = q'qqq.' AEROTHERMODYNAMIC ANALYSIS OF A FANJET'SI UNITS'Ca 'm/s'Flight velocity'Tahffff@'K'Ambient temperature'Pa8gDio? 'Bar'Ambient pressure 'Fuel HVc 'kJ/kg'Heating value 'Cpa  'kJ/kg'Air heat capacity 'Cpa/CpgZ&? l?!'Air/gas heat capacity ratio 'OPR&'Overall pressure ratio 'FPR  'Fan pressure ratio 'LPCPR %, 'Low pressure compressor pressure ratio 'HPCPR$ hM6d@   'HPCPR = OPR/[FPR(LPCPR)] 'B  'Bypass Ratio 'mair  'kg/s 'Inlet total mass flow rate 'cpeta%0'Compressor and fan polytropic efficiencies'(n-1)/n|c((?e3'(n-1)/n|c = (k-1)/[k*cpeta] (for fan & comp.) 'tpeta%#'Turbine polytropic efficiency'n/(n-1)|t88@/'Turbine polytropic factor, k/[(k-1)tpeta]'(dp/p)|c('Combustor fractional pressure drop 'To5'C+'High press. turbine inlet temperature 'To5 @"'K'To5 (K) = To5 (C) + 270 'To1=Toa0(sg@'K'Toa=Ta+Ca^2/(2*Cpa*1000)'Poa = Po1(T]?e 'Bar!'Po1 = Poa = Pa*(Toa/Ta)^3.5 'Po28匈?  'Bar'Po2=FPR*Po1 'Po3@X@ъ?  'Bar'Po3=(LPCPR)Po2 'Po4x7ٟ@  'Bar'Po4=Po3(HPCPR) 'Po5!PZcu@ 'Bar'Po5=Po4*[1 - comb(dp/p)] 'To2#p*@ 'K'To2=To1*FPR^[(n-1)/n]|c 'To3$w@ 'K!'To3=To2*(LPCPR)^[(n-1)/n]|c 'To4# }혖@ 'K'To4=To3*HPCPR^[(n-1)/n]|c 'To6+XA, @'K!'To6=To5-(Cpa/Cpg)*(To4-To3) 'To7FE+@ 'K1'To7=To6-(Cpa/Cpg)[(B+1)(To2-To1)+(To3-To2)] 'Po6+ ` Č@ 'Bar# 'Po6=Po5*(To6/To5)^[n/(n-1)]|t !'Po7+!*e?  !'Bar#!'Po7=Po6*(To7/To6)^[n/(n-1)]|t "'Po7/Pc8$"X["?1"'Crit. press. ratio: Po7/Pc8={[(4/3)+1]/2}^4 #'Po7/Pa4#86@!!**Po7&#&#; ('m/s3('IF (Po7/Pc8)<(Po7/Pa) THEN C8=(287*T8*4/3)^.5*)' ELSE C8 = [(To7-T8)*2000*Cpg)]^.5*'P80*F?#"!"; *'Bar0*'IF Pc8>Pa THEN P8=Po7/(Po7/Pc8) ELSE P8=Pa +'Rho8%+@O]?*#& +'kg/m^3+'Rho8=100*P8/(.287*T8) ,'A8/m8!,>L?(+,'m^2-s/kg,'A8/m8=1/(C8*Rho8)-'T9J-hY@%$ %e;-'K$-'IF Pc9>Pa THEN T9=2To2/(7/5+1)%.' ELSE T9=To2/(Po2/Pa)^(1/3.5)/'C9J/mE[@%$>- #-#; /'m/s(/'IF Pc9>Pa THEN C9=(287*T8*7/5)^.5 &0' ELSE C=[(To2-T9)*2000*Cpa]^.51'P901R?ɫ?%$$; 1'Bar01'IF Pc9>Pa THEN P9=Po2/(Po2/Pc9) ELSE P9=Pa 2'rho9%28S?1#- 2'kg/m^32'Rho9=100*P9/(.287*T9) 3'A9/m9!3?@pv?/23'm^2-s/kg3'A9/m9=1/(C9*Rho9)4'Specific4X|@(/  *,13    4'N-s/kg-4'ST = {C8+C9*B-Ca*(B+1)+[(P8-Pa)*(A8/m8)5'Thrust,ST)5' +(P9-Pa)*(A9/m9)*B]*10^5}/(B+1) 6'Thrust6̽ @ 46'N-6'Total engine thrust= mair(spec. thrust) 7'f/a377>?7'f/a=Cpg(To5-To4)/HV 8'mfuel(8x7e? 7  8'kg/s%8'Fuel flow rate=mair*(f/a)/(1+B) 9'TSFC)9ÍŠ?74  9'kg/N-s%9'TSFC=(f/a)/[spec. thrust)(B+1)] :'TSFC':1vM? 9 :'kg/N-hr:'TSFC'=3600 TSFC;'ST|core mr;X|@(/  *,13   ;'N-s/kg;'ST based on m8 = (B+1)ST