Fig.1

Improvement in installation specific fuel consumption of Variable Cycle Engine （VCE）［2］

Fig.2

Installation performance calculation model of propulsion system

Fig.3

Typical components of ACE with rear variable fan

Fig.4

Two working modes’ flow path of ACE with rear variable fan

Fig.5

Adjustable components of ACE with rear variable fan

Fig.6

Multi-angle characteristics of corrected rotating speed-corrected airflow-pressure ratio for rear variable fan

Table 1

Design cycle parameters

Fig.7

Calculation flow of design point

Fig.8

Calculation process of installation performance

Fig.9

Matched total pressure recovery coefficient

Fig.10

Matched airflow coefficient

Fig.11

Bypass mass flow coefficient

Fig.12

Total pressure recovery coefficient

Fig.13

Boundary layer bleed airflow coefficient

Fig.14

Spillage drag coefficient

Fig.15

Bypass drag coefficient

Fig.16

Boundary layer bleed drag coefficient

Fig.17

Gross thrust coefficient of nozzle

Fig.18

Nozzle/aftbody drag coefficient in complete expansion condition

Fig.19

Amendatory nozzle/aftbody drag coefficient

Table 2

Allowable ranges of variable components

Fig.20

Supersonic inlet types in library of inlet/nozzle configurations and performance

Table 3

Inlet critical parameters

Fig.21

Maximum capture areas in different Mach numbers

Table 4

Capture areas in different configurations of inlets

Fig.22

Total recovery coefficient of different inlets in cruise conditions

Fig.23

Outflow drag of different inlets in cruise conditions

Fig.24

Configuration diagrams of two nozzles

Fig.25

Geometry of axisymmetric convergent-divergent nozzle

Fig.26

Nozzle outlet areas in supersonic cruise condition

Fig.27

Aftbody drag comparison of convergent-divergent nozzle in two size-constraint schemes

Fig.28

Installation performance comparison of convergent-divergent nozzle in two size-constraint schemes

Fig.29

Aftbody drag comparison of plug nozzle in two size-constraint schemes

Fig.30

Installation performance comparison of plug nozzle in two size-constraint schemes

Fig.31

Installation performance comparison of convergent-divergent nozzle and plug nozzle in supersonic cruise condition

Fig.32

Principal diagram of optimization design method

Fig.33

Throttling characteristic comparison of two optimization methods in supersonic cruise condition

Table 5

Fitting functions’ critical parameters of two methods in supersonic cruise condition during double outer bypass mode

Table 6

Fitting functions’ critical parameters of two methods in supersonic cruise condition during triple outer bypass mode

Fig.34

Inlet outflow drag comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.35

Nozzle/aftbody drag comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.36

Inner flow drag comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.37

Inlet outflow drag comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.38

Inlet airflow comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.39

Nozzle expansion ratio comparison of two methods in supersonic cruise condition during double outer bypass mode

Fig.40

Thrust coefficient application area in supersonic cruise condition during double outer bypass mode

Fig.41

Optimal throttling line comparison of two methods in supersonic cruise condition

Table 7

Optimal throttling line fitting functions’ critical parameters of two methods in supersonic cruise condition

Fig.42

Throttling characteristic comparison of two

Table 8

Critical parameters of fitting functions of two methods in subsonic cruise condition during double outer bypass mode

Table 9

Critical parameters of fitting functions of two methods in subsonic cruise condition during triple outer bypass mode

Fig.43

Optimal throttling line comparison of two methods in subsonic cruise condition

Table 10

Optimal throttling line critical parameters of fitting functions of two methods in subsonic cruise condition

Table 11

Selecting sample points for velocity-altitude characteristics

Table 12

Curved surface critical parameters of fitting functions of two methods for velocity-altitude characteristics below Mach number 0.9

Fig.44

Maximum thrust fitting curved surface of velocity-altitude characteristics below Mach number 0.9

Fig.45

Installation thrust of velocity-altitude characteristics above Mach number 0.9

Fig.46

Optimization design process of propulsion system characteristics