Ideal Turbofan Calculator

Based on Hill and Peterson, Mechanics and Thermodynamics of Propulsion

Inputs
SymbolValueMeaning
M(-) Flight Mach number
Ta(K) Ambient temperature
pa(Pa) Ambient pressure
prc(-) Compressor pressure ratio
prb(-) Burner pressure ratio
prf(-) Fan pressure ratio
Qr(J/kg) Heating value of fuel
T04(K) Turbine inlet temperature
beta(-) Turbofan bypass ratio
gamma(-) Sp. heat ratio (ambient air)
gamma_d(-) Sp. heat ratio (diffuser)
gamma_f(-) Sp. heat ratio (fan)
gamma_c(-) Sp. heat ratio (compressor)
gamma_b(-) Sp. heat ratio (burner)
gamma_t(-) Sp. heat ratio (turbine)
gamma_n(-) Sp. heat ratio (nozzle)
eta_d(-) Efficiency (diffuser)
eta_c(-) Efficiency (compressor)
eta_t(-) Efficiency (turbine)
eta_n(-) Efficiency (nozzle)
eta_f(-) Efficiency (fan)
eta_fn(-) Efficiency (fan nozzle)
Results
SymbolValueMeaning
T02240.30(K) Compressor Inlet Temperature
p0226942.20(Pa) Compressor Inlet Pressure
T03665.97(K) Compressor Outlet Temperature
p03808265.90(Pa) Compressor Outlet Pressure
f2.02e-2(-) Burner fuel-to-air ratio
p04808265.90(Pa) Turbine inlet pressure
T05952.62(K) Turbine outlet temperature
p05108771.25(Pa) Turbine outlet pressure
T08270.73(K) Fan outlet temperature
p0840413.30(Pa) Fan outlet pressure
u220.95(m/s) Flight velocity
ue867.91(m/s) Nozzle exit velocity
uef322.40(m/s) Fan nozzle exit velocity
Tma1070.28(N/kg/s) Thrust per air mass flow rate
TSFC1.89e-5(kg/s/N) Fuel flow rate per thrust

Performance plots

Note, many settings for these plots are hard-coded to correspond to the homework set. I suggest you download and edit the source code.

Propulsion Efficiency

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Takeoff at Sea Level

Cruise at M=0.85 @ 40,000 ft

Effect of Efficiencies on Specific Thrust (Takeoff)

Effect of Efficiencies on TSFC (Takeoff)