Fig.1

Locations of entry and exit of three-dimensional nozzle within a parent flowfield

Fig.2

Mach number contour plots of axisymmetric maximum thrust parent flowfield

Fig.3

Bevelling angle definition method of three-dimensional single expansion ramp nozzle

Fig.4

Three-dimensional nozzles generated by connecting streamlines

Fig.5

Performance curves of nozzle corresponding to different bevel angles

Fig.6

Three-dimensional nozzle with circular-to-rectangular shape transition

Fig.7

Sketch of over-under TBCC exhaust system

Fig.8

Sketch of rotating ramp

Fig.9

Thrust performance of exhaust system varies with geometric parameters of rotating ramp

Fig.10

Dual-flowpath adjustable exhaust system model

Fig.11

Exhaust system model of separate operation of ramjet

Table 1

Test condition parameters for typical operating points

Fig.12

Computational grid and boundary conditions

Fig.13

Mach number contours of symmetry plane at test point 1

Fig.14

Mach number contours of 3D flow field at test point 1

Fig.15

Mach number contours of symmetry plane at test point 2

Fig.16

Mach number contours of 3D flow field at test point 2

Fig.17

Comparison of experimental static pressure data with CFD prediction at test point 1 and 2

Fig.18

Mach number contours of symmetry plane and experimental schlieren image at test point 3

Fig.19

Mach number contours of 3D flow field at test point 3

Fig.20

Flow structure in the exhaust system at test point 3 （based on Q criterion and Q=1×109 s-2）

Fig.21

pressure distribution of test point 3

Fig.22

Mach number contours of symmetry plane and Experimental schlieren image at test point 4

Fig.23

Mach number contours of 3D flow field at test point 4

Fig.24

pressure distribution of test point 4

Fig.25

Mach number contours of symmetry plane and experimental schlieren image at test point 5

Fig.26

Mach number contours of 3D flow field at test point 5

Fig.27

Pressure distribution of test point 5

Fig.28

Mach number contours of symmetry plane and 3D flow field at test point 6-8

Fig.29

Experimental schlieren image at test point 6-8

Fig.30

Pressure distribution of test point 6-8

Fig.31

Thrust coefficient over flight envelop