Fig. 1

Generic cycle of loosely coupled algorithm

Fig. 2

Time-averaged skin friction coefficient over flexible panel

Fig. 3

Fluid-structural coupling calculation model of flexible panel in shock/boundary layer interaction

Fig. 4

Effect of grid resolution and time step size on panel oscillation at3/4chord of flexible panel in shock/boundary layer interaction（xi/a=0.4）

Fig. 5

Vibration response at 3/4 chord of flexible panel

Fig. 6

Spectrum of vibration at different positions of panel

Fig. 7

Mean and selected instantaneous panel shapes，and x-t diagram of panel deflections

Fig. 8

Pressure contour and density contour for panel flutter at Φ=180°

Fig. 9

Effect of panel flutter on flow separation（xi/a=0.4）

Fig. 10

Skin-friction along panel and instantaneous pressure distribution on panel

Fig. 11

Streamwise velocity contours for xi/a=0.4 and over flexible panel and rigid-flat panel（Scale has been magnified by factor of 10 in y-direction）

Fig. 12

Velocity distribution along different axial positions in computational domain

Fig. 13

Effect of shock impingement location on panel flutter

Fig. 14

Power spectrum analysis of panel flutter

Fig. 15

Comparison of pressure difference between upper and lower surface of panel

Fig. 16

Mean deformation distribution of panel

Fig. 17

Comparison of vibration velocity in y-direction and pressure response at 3/4 chord of panel

Fig. 18

Effect of shock impingement location on flow separation

Fig. 19

Separation length normalized by corresponding rigid-flat panel result

Fig. 20

Skin-friction along panel with xi/a=0.35

Fig. 21

Streamwise velocity contours for xi/a=0.35 and over flexible panel and rigid-flat panel（Scale has been magnified by factor of 10 in y-direction）

Fig. 22

Pressure contours at Φ=180° under different working conditions（Scale has been magnified by factor of 10 in y-direction）

Fig. 23

Velocity distribution curves of different axial positions along y at Φ=180°