Table 1

Shock wave/boundary layer interaction control methods and corresponding mechanisms

Fig.1

Schematic diagram of shock wave/boundary layer interaction［1］

Fig.2

Schematic illustration of detail classification for flows in SWBLI［43］

Fig.3

Diagram of vortex structure downstream curved compression ramp［51］

Fig.4

Contours of root-mean-square schlieren for SWBLI at Re2［52］

Fig.5

Schlieren images of SWBLI at Ma∞=2［43］

Fig.6

Comparison of scale rule example verification and experimental schlieren［53］

Fig.7

Spatial evolution of Görtler-like vortices in compression ramp［54］

Fig.8

Instantaneous velocity fields［55］

Fig.9

Velocity profile at different streamwise distance along plate［57］

Fig.10

Effect of shock control bump［60］

Fig.11

Bump geometric shape

Fig.12

Schematic diagram of SWBLI with and without bump［60］

Fig.13

Wing with three-dimensional bumps array［65］

Fig.14

Vorticity structure for off-design shock positions［61］

Fig.15

Generation of streamwise vortices under off-design conditions［61］

Fig.16

Composite image of schlieren and oil flow diagram for baseline SCB［66］

Fig.17

Diagram of bump construction［69］

Fig.18

Sketches of 3D adaptive SCB experiment model［73］

Fig. 19

Bump shapes for four different positions （3D surface deformations from photogrammetry）［73］

Fig.20

Fuselage surface mesh， and fuselage surface streamline and pressure distribution （α=5°）［85］

Fig.21

Fighters with Bump inlet

Fig.22

Configuration diagram of three typical bulges， Mach number contour， vorticity contour［87］

Fig.23

View of model and isometric view of sensor locations［88］

Fig.24

Schlieren images of shock formation under different operating conditions， IBAR=0.23-0.85， α=β=0°［90］

Fig.25

Numerical simulation and test model of 3D bump-integrated IWI［92］

Fig.26

3D view of surface pressure of bumps［93］

Fig.27

Near wall streamline distributions of inlets with different bump heights at Ma =3.5［94］

Fig.28

SWBLI control method with deformable bump［7］

Fig.29

Experimental schlieren image of SWBLI control by two-dimensional bump［7］

Fig.30

SWBLI control by two-dimensional bump in hypersonic inlet［8］

Fig.31

Experimental results of SWBLI control with deformable bump［9］

Fig.32

Sketches of test model with concave bump and shock generator and experimental schlieren images［6］