Fig.1

Schematic diagram of typical hypersonic propulsion system at higher Mach number

Fig.2

Schematic diagram of basic flowfield structure for inlet fuel pre-injection/mixing［10］

Fig.3

X-43A flight demonstrator and engine［15］

Fig.4

Hyshot-2 engine and test wall pressure［18］

Fig.5

Hifire-2 engine［23］

Fig.6

HEXAFLY-INT engine［25］

Fig.7

Shock-induced combustion engine［31］

Fig.8

Oblique detonation engine［33］

Fig.9

Typical injection method for supersonic inflow［34］

Fig.10

Schematic of a transverse sonic jet into supersonic flow［35］

Fig.11

Density gradient and mass fraction contour at central surface for turbulent and laminar crossflow［40］

Fig.12

Typical shocks and flow features of transverse injection in supersonic flow obtained by large eddy simualtion［42］

Fig.13

Experiment model and results

Fig.14

Scramjet model for numerical simulation［59］

Fig.15

Mixing efficiency for different injection methods［59］

Fig.16

Axisymmetrical duel-mode scramjet model［60］

Fig.17

Two-dimensional generic scramjet model and experimental results［63］

Fig.18

REST three-dimensional inward-turning scramjet model

Fig.19

Wall pressure distribution for typical cases of REST scramjet model［65］

Fig.20

Front view of REST scramjet mounted in T4 shock-tunnel test section［66］

Fig.21

Thrust coefficient V.S. equivalence ratio for three fuel injection schemes［66］

Fig.22

Tailored injetor layout［74］

Fig.23

Cantilevered injector and improved configuration for suppression ignition［76］

Fig.24

Schematics of radical farming and shock-induced combustion［5］

Fig.25

Thermal compression scramjet model with inlet fuel pre-injection［79］

Fig.26

High-Mach-number scramjet model mounted in JF-12 wind tunnel［80］

Fig.27

High-Mach-number scramjet experiment in FD-14A wind tunnel［81］

Fig.28

Ground tests conducted by China Academy of Aerospace Aerodynamics［82］

Fig.29

Schematic of external injection［83］

Fig.30

Schematic of designed ODE flowpath［84］

Fig.31

Oblique detonation tests with pre-injection conducted by Institute of Mechanics， Chinese Academy of Sciences［83］

Fig.32

Test flowfields of oblique detonation engine［83］

Fig.33

Pressure contour of typical detonation combustion mode［84］

Fig.34

Mach number of inlet contours for 3 cases［85］

Fig.35

Numerical schlieren comparison for nitrogen injection and powder-fuel injection［86］

Fig.36

Effects of inlet pre-injection on compression shock wave at Ma=10 condition［87］

Fig.37

Schematic diagram of scramjet engine with inlet pre-injection active cooled inlet［93］

Fig.38

Cantilevered Injector configuration［68］

Fig.39

Schematic of fuel pre-injection jet flow structure［99］

Fig.40

Borghi diagram of burner structures （Dat vs Ret）［111］

Fig.41

Basic development ideas of hypersonic inlet pre-injection

Fig.42

Schematic diagram of inlet pre-injetction experiment in wind tunnel