Fig.1

Supersonic civil aircraft of TU-144

Fig.2

“Concorde” supersonic civil aircraft

Fig.3

Aerodynamic layout of supersonic civil aircraft abroad

Fig.4

Design method of three-dimensional inward turning inlet

Fig.5

Integrated design of supersonic civil aircraft and engines

Fig.6

Structural mesh and boundary condition of three-dimensional inward turning inlet cowl

Fig.7

Trim mesh of supersonic civil aircraft

Fig.8

Monitoring surface of three-dimensional inward turning inlet

Fig.9

Process of nonlinear “BoomProp” calculation for predicting sonic boom signal

Fig.10

AXIE 3D verification model and sonic boom signal extraction location

Fig.11

Comparison of AXIE far field sonic boom intensity results calculated by “BoomProp” and “sBoom” program［49］

Table 1

Aerodynamic results of inlet under different mesh densities

Fig.12

Contours of pressure distribution on symmetry surface of inlet

Fig.13

Verification of independence of pressure distribution in three-dimensional inward turning inlet

Fig.14

Verification of independence of sonic boom in integrated design of civil aircraft

Fig.15

Pressure distribution contours on symmetry surface of integration design under different mesh densities

Table 2

Design conditions of different inlets

Table 3

Geometric structure of the inlet cowl

Fig.16

Design of three-dimensional inward turning inlet cowl

Fig.17

Contours of aerodynamic performance on the outlet of inlet with different cowls

Table 4

Aerodynamic performances of outlet in different inlets

Table 5

Results of pressure distribution differences in far field of different inlets

Fig.18

Pressure distribution curves on inlet monitor surface under different conditions

Fig.19

Bars charts of sonic boom intensity on inlet monitor surface under different conditions

Fig.20

Bars charts of pressure distribution on the inlet monitor surface under different Mach numbers

Fig.21

Mach number contours of inlet symmetry surface under different calculation conditions

Fig.22

Design principle of curvature change of inlet cowls

Fig.23

Pressure distribution curves on monitor surface in inlets with different cowl surfaces

Fig.24

Pressure distribution contours at X=12 m surface in different inlets

Fig.25

Bar charts of pressure distribution on monitor surfaces in different integrated designs of civil aircrafts

Fig.26

Mach number contours on the engine mid-section under different conditions

Fig.27

Sonic boom intensity curves in different integrated designs of civil aircraft

Fig.28

Bar charts of sonic boom in different integrated designs of civil aircrafts

Fig.29

Pressure distribution contour on symmetry surface of integrated design

Fig.30

Sonic boom curves of integrated designs for different layouts on monitor surface at H/L=2.0

Fig.31

Pressure distribution and Mach number contours of different integrated design layouts on engine mid-section

Fig.32

Pressure distribution contours of different integrated design layouts at symmetry surface