Fig.1

Schematic of sonic boom prediction method for near-field prediction coupled far-field propagation

Fig.2

Flow of JSGD anti-design method［16］

Fig.3

Mixed reliability anti-design process based on PNFO

Fig.4

Three-view drawing of layout scheme （XC-01）

Fig.5

Design features of XC-01 layout

Fig.6

Overpressure distribution of XC-01 layout

Fig.7

Far-field and near-field sonic boom signal at triploid body length below XC-01 layout

Fig.8

Body profile comparison of XC-01 layout and XC-02 layout

Fig.9

Equivalent cross-sectional area matching

Fig.10

Near-field and far-field sonic boom signal below aircraft （Ma=1.6， H=16 km）

Fig.11

Flow field characteristics of shock wave and expansion wave

Fig.12

Shock wave and expansion wave reflection in near-field sonic boom signal

Fig.13

Comparison of XC-02 and XC-03 layouts

Fig.14

Flow field characteristics of XC-02 and XC-03 layouts at symmetric surface

Fig.15

Far-field and near-field sonic boom signal sonic boom signal below aircraft of XC-02and XC-03 layouts

Fig.16

Converted equivalent area comparison of XC-03 and XC-04 layouts

Fig.17

Body profile comparison of XC-03 and XC-04 layouts

Fig.18

Far-field and near-field sonic boom signal sonic boom signal below aircraft of XC-03and XC-04 layouts

Fig.19

Three times low sonic boom design

Fig.20

Flow field characteristics of XC-01 and XC-04 layout at symmetric surface

Fig.21

Afterbody flow field analysis of XC-04 and XC-04 layouts

Fig.22

Comparison of near-field sonic boom signal at triploid body length below XC-01 and XC-04 layout

Fig.23

Propagation process of sonic boom signal of XC-01 and XC-04 layouts

Fig.24

Comparison of far-field sonic boom signal of XC-01 and XC-04 layouts

Fig.25

Ground waveform spectral distribution of XC-01 and XC-04 layouts

Fig.26

Comparison of near field waveform at 20°and 40° circumferential angle of XC-01 and XC-04 layouts

Fig.27

Comparison of far field waveform at 20° and 40° circumferential angle of XC-01 and XC-04 layouts

Fig.28

Comparison of perceived loudness in decibel of sonic boom tapestry between XC-01 and XC-04 layouts

Fig.29

Aerodynamic characteristics of XC-01 and XC-04 layouts

Fig.30

Perceived loudness in decibel at different heights

Fig.31

Perceived loudness in decibel at different heights at 0° circumferential angle

Fig.32

Far-field propagation waveform at different heights

Fig.33

Perceived loudness in decibel at different Mach numbers

Fig.34

Perceived loudness in decibel at different Mach numbers at 0°circumferential angle

Fig.35

Comparison of actual and theoretical equivalent cross-sectional areas at different inner wing swept angles and different outer wing swept angles

Fig.36

Perceived loudness in decibel at different inner wing swept angles and different outer wing swept angles

Fig.37

Aerodynamic characteristics at different Mach numbers

Fig.38

Aerodynamic characteristics at different flying heights