Research Article
Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept
Table 8
Turbofan mode optimization scheme.
| | Design point (mode transition point) | Before optimization | After optimization |
| | Flight altitude (km) | 20.9 | 20.9 | | Flight Mach | 3 | 3 | | Thrust (kN) | 151.8 | 157 | | SFC (kg/daN/h) | 1.61 | 1.62 | | Air mass flow (kg/s) | 318 | 318.5 | | Bypass ratio | 0.7 | 0.74 | | Outlet temperature of the main combustion chamber (K) | 2000 | 2000 | | Afterburner temperature (K) | 1350 | 1377 |
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