Fig.1

Model of shock vectoring control serpentine nozzle

Table 1

Parameters of shock vectoring control serpentine nozzle

Fig.2

Computational domain grid of shock vectoring control serpentine nozzle

Table 2

Flow field boundary parameters

Fig.3

Discrete transfer method schematic diagram

Fig.4

Location of detection points

Fig.5

Model of serpentine nozzle for test

Fig.6

Nozzle infrared radiation characteristics test platform

Fig.7

Comparison of numerical simulation and test results

Fig.8

Infrared radiation intensity distribution of shock vectoring control serpentine nozzle

Fig.9

Mach number distribution on symmetry plane

Fig.10

Static temperature and dimensionless static pressure distribution on symmetry plane

Fig.11

Temperature distribution of nozzle wall

Fig.12

Visibility of nozzle wall from a specific perspective

Fig.13

Visibility of nozzle wall at different detection angles on horizontal plane

Fig.14

Visibility of nozzle wall at different detection angles on the upper half of vertical plane

Fig.15

Gas path at different detection angles on vertical plane

Fig.16

Visibility of gas inside nozzle at different detection angles on vertical plane

Fig.17

Projected area of 550 K isosurface in gas domain and plume cross-section on the upper half of vertical plane

Fig.18

Visibility of nozzle wall at different detection angles on the lower half of vertical plane

Fig.19

Projected area of 550 K isosurface in gas domain and plume cross-section on the lower half of vertical plane

Fig.20

Infrared radiation intensity distribution on horizontal plane under different operating modes

Fig.21

Infrared radiation intensity distribution on vertical plane under different operating modes

Fig.22

Static temperature distribution on symmetry plane and nozzle wall under different operating modes

Fig.23

Static temperature and Mach number distributions of plume on symmetry plane under different operating modes

Fig.24

Infrared radiation intensity distribution on horizontal plane under different SPR

Fig.25

Infrared radiation intensity distribution on vertical plane under different SPR

Fig.26

Mach number distribution on symmetry plane under different SPR

Fig.27

Temperature distribution of upper wall ridge line under different SPR

Fig.28

Deflection angle of plume and relative pressure difference at exit under different SPR

Fig.29

Mach number distribution and Ma=0.6 contour lines in farfield under different SPR

Fig.30

Thrust vector angle and thrust coefficient under different SPR

Fig.31

Reduced flow rate ratio of secondary flow and thrust vectoring efficiency under different SPR