Fig.1

Mesh topology of C608 aircraft

Fig.2

C608 aircraft nearfield overpressure signal calculation results

Fig.3

Predictions of ground perceived sound level of C609 aircraft

Fig.4

Predictions of ground overpressure signal of C609 aircraft

Fig.5

Schematic of low-boom aerodynamic design process

Fig.6

Typical mission profile for long-range supersonic airliner

Table 1

DTO of airliners （at ISA sea level， calm wind， dry runway， WMTO）

Table 2

Design requirements for long-range supersonic airliner

Fig.7

Sketch of engine model with main parameters

Table 3

Parameters of a modern low-bypass engine and present engine

Table 4

Engine performance under typical conditions

Fig.8

Weight data of supersonic aircrafts

Fig.9

Relationship between standard range and maxmium takeoff mass for various lift-to-drag ratios

Fig.10

Distribution of fuel tanks and center of gravity shift range

Table 5

Aerodynamic parameter values for layout design

Fig.11

Limitations and selection of wing loading and thrust-to-weight ratio

Fig.12

Equivalent area distribution of Configuration A（Ma=1.6）

Fig.13

Volumetric equivalent area distribution of configuration A （Ma=1.0）

Fig.14

Plan views of Configuration A

Fig.15

Wave distributions in symmetry plane of Configuration A

Fig.16

Near-field signal of target and improvement scheme of fuselage

Fig.17

Propagation of overpressure signal of Configurations A and B

Fig.18

Nearfield overpressure signals of Configuration C

Fig.19

Geometry of tail bump and quiet spike of Configuration C

Fig.20

Wave distributions in symmetry plane of Configurations B and C

Fig.21

Propagation of overpressure signal of Configurations B and C

Table 6

Ground perceived level of present configurations

Fig.22

Lift-dray ratios of Configuration C at various Mach numbers

Fig.23

Thrust available， required thrust， lift-drag ratio vs Mach number

Fig.24

Pitch moment coefficients of Configuration C at various March numbers

Fig.25

Yaw moment coefficients of Configuration C at various angles of attack

Fig.26

Pathlines of engine intake at cruise condition

Fig.27

Geometry of through-flow nacelle and nacelle with an inlet cone and its supports

Fig.28

Demonstration of fuselage vortex location