Fig.1

Schematic diagram of scramjet structure［2］

Fig.2

Schematic diagram of transverse jet profile in supersonic flow［23］

Fig.3

Comparison of specific impulse of different propulsion systems［25］

Table 1

Representative research on low Mach number scramjet flow and combustion characteristics

Fig.4

CH* photometric graph at different moments ［41］

Fig.5

Contours of Mach number with different hydrogen equivalent ratios［42］

Fig.6

Variations curves of combustor parameters in mode transition process［44］

Fig.7

Time-averaged flame chemiluminescence images， time-averaged schlieren images and instantaneous schlieren images with different cavity length to depth ratios［47］

Fig.8

Flow field schlieren images of different equivalence ratios and injector position cases［49］

Fig.9

Comparison of flame front shapes in different discharge modules［80］

Fig.10

Instantaneous 3D flow structures［50］

Fig.11

Schematic diagram of typical ramp flow structure［81］

Fig.12

Contours of mole fraction distribution of fuel in transverse plane［83］

Table 2

Representative research on high Mach number scramjet flow and combustion characteristics

Fig.13

Thrust coefficient as function of equivalence ratio for all fuel injection schemes［88］

Fig.14

Distribution of N2 mass fractions［92］

Fig.15

Schematic diagram of “Radical farming” mode［106］

Fig.16

Maximum specific thrust at different freestream Mach numbers［94］

Fig.17

OH* PLIF images in ethylene-fueled experiments［95］

Fig.18

OH∗ chemiluminescence map in axisymmetric scramjet model superimposed on schlieren image［97］

Fig.19

Numerical schlieren for different injection methods［98］

Fig.20

Contours of mixture fraction （left） and vibrational temperature （right） in thermodynamic nonequilibrium state［99］

Fig.21

3D supersonic flame structure in thermodynamic equilibrium and nonequilibrium states［102］

Fig.22

Mass fraction contours of transient water vapor in thermodynamic equilibrium （top） and nonequilibrium （bottom） states［102］

Fig.23

Temperature and pressure curves in different cases［103］

Table 3

Representative study on wide speed range scramjet flow and combustion characteristics

Fig.24

Temperature contours in Ma=6 （left） and Ma=12 （right） cases［116］

Fig.25

Chemiluminescence image of different equivalent ratios［119］

Fig.26

Typical injector shape and streamlines［134］

Fig.27

Schematic diagram of typical combustion modes［137］

Fig.28

Instantaneous photometric images of typical combustion modes［125］

Fig.29

Best performance boundary in wide range of flight conditions［126］

Fig.30

Schlieren images of cold flow field in different supersonic combustors［130］