Fig.1

Schematics of combustor configuration and diameters for axisymmetric scramjet

Table 1

Operating conditions of supersonic inflow and fuel jets

Fig.2

Schematic diagram of computational domain and boundary conditions

Fig.3

Calculated wall pressure profiles using meshes with different sizes

Fig.4

Comparison of experimental wall pressures in non-jet plane at two equivalence ratios of 0.18 and 0.06 with RANS calculations， with calculated Mach number contours

Fig.5

Comparison of experimental time-averaged broad-spectrum chemiluminescence images with simulated heat release rate spanwise integral contours at two equivalence ratios of 0.18 and 0.06

Fig.6

Combustion flow field streamlines， density gradients and mixture fraction distributions at two equivalence ratios of 0.18 and 0.06

Fig.7

Contours of heat release rate in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.8

Contours of OH distribution in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.9

CO2 distribution contours in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.10

Contours of H2O distribution in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.11

Contours of CO distribution in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.12

Spatial distributions of combustion products in mixture fraction coordinate for different flow positions （X = 0.24， 0.30， 0.36 m） at 0.18 equivalence ratio

Fig.13

Spatial distributions of combustion products in mixture fraction coordinate for different flow positions （X = 0.24， 0.30， 0.36 m） at 0.06 equivalence ratio

Fig.14

Characteristics of one-dimensional distribution of combustion flow field parameters at 0.18 equivalence ratio

Fig.15

Characteristics of one-dimensional distribution of combustion flow field parameters at 0.06 equivalence ratio

Fig.16

Contours of Flame Index distribution in combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.17

Kernel density estimates of Flame Index versus logarithm of heat release rate for combustion flow field at two equivalence ratios of 0.18 and 0.06

Fig.18

Kernel density estimates of Mach number versus logarithm of heat release rate for combustion flow field at two equivalence ratios

Fig.19

Scatterplot of mixture fraction versus progress variables in combustion flow field at 0.18 equivalence ratio