Fig.1

Geometry model of aircraft and missile

Fig.2

Schematic diagram of aircraft angle of attack and initial installation angle of missile

Fig.3

Computational domain and boundary conditions

Fig.4

Mesh around aircraft and nose boundary layer

Fig.5

Temperature variation curve with altitude［31］

Table 1

Environmental parameters at altitude of 25， 30 and 35 km

Table 2

Information and calculation parameters of aircraft and missile

Fig.6

Vortex structures at different angles of attack for Ma=8

Fig.7

Pressure contour on aircraft belly at different angles of attack for Ma=8

Fig.8

Streamline variation around aircraft under different conditions

Fig.9

Variation of missile displacement， angular displacement， aerodynamic force， and aerodynamic moment at five angles of attack

Table 3

Comparison of missile displacement and angular displacement at different angles of attack at П= 0.2 s （Ma=8）

Fig.10

Missile position variation at five angles of attack

Fig.11

Effect of flight altitude on missile separation displacement and angular displacement

Fig.12

Position variation of missile at different flight altitudes

Table 4

Comparison of missile displacement and angular displacement at different flight altitudes at П= 0.2 s

Fig.13

Separation schematic diagram of missile internally embedded in aircraft belly and externally mounted on aircraft side

Fig.14

Static pressure contour around aircraft and missile at different altitudes

Fig.15

Effect of initial installation angle on missile displacement and angular displacement

Table 5

Comparison of missile displacement and angular displacement at different initial installation angles at П= 0.2 s

Fig.16

Aerodynamic force and aerodynamic moment of missile at different initial installation angles

Fig.17

Position variation of missile at different installation angles

Fig.18

Effect of ejection force magnitude on missile displacement and angular displacement

Table 6

Comparison of missile displacement and angular displacement at different ejection force magnitude at П=0.2 s

Fig.19

Position variation of missile at four force magnitude

Fig.20

Effect of ejection force action time on missile displacement and angular displacement

Fig.21

Position variation of missile at four force action time