Fig. 1

Test model of MR2.4［31］

Fig. 2

Simplified model of canard

Table 1

Simulated flight conditions

Fig. 3

Computational domain and boundary conditions setting

Fig. 4

Schematic of wingtip vortex/oblique shock wave interaction

Table 2

Three sets of grids used in supersonic flow

Fig. 5

Comparison of pressure curves obtained by grids of different resolutions

Table 3

Grid used in subsonic flow

Fig. 6

Comparison between numerical and experimental data in subsonic flow

Fig. 7

Comparison between numerical and experimental data in supersonic flow

Fig. 8

Comparison of experimental and present numerical results of interaction between streamwise vortex and oblique shock wave

Fig. 9

Three-dimensional structure of wingtip vortex （iso-surface of streamwise vorticity）

Fig. 10

Tangential velocity profiles at various flow conditions

Fig. 11

Tangential velocity profiles at Ma∞=6.0 with different angles of attack

Fig. 12

Comparison of circulation profiles

Fig. 13

Circulation profiles at various flow conditions

Fig. 14

Circulation profiles at Ma∞=6.0 with different angles of attack

Fig. 15

Variations of swirl number along streamwise direction at different Ma∞ （α=6°）

Fig. 16

Variations of swirl number along srteamwise direction at different angles of attack（Ma∞=6.0）

Table 4

Physical parameters of wingtip vortex at typical locations in Ma∞=2 flow

Table 5

Physical parameters of wingtip vortex at typical locations in Ma∞=4 flow

Table 6

Physical parameters of wingtip vortex at typical locations in Ma∞=6 flow

Fig. 17

Typical three-dimensional flowfield of vortex breakdown

Fig. 18

Streamlines superimposed on Mach number contours near vortex core of vortex breakdown

Fig. 19

Three-dimensional flowfield of vortex non-breakdown

Fig. 20

Streamlines superimposed on Mach number contours near vortex core of vortex non-breakdown

Fig. 21

Theoretical prediction of vortex breakdown