Fig.1

Flow field around a wave cancellation biplane at AoA=0°

Fig.2

Flow field pressure and Mach number contour maps of wave cancellation biplane with MaD=3 and AoAD=0°

Fig.3

Comparison of inviscid CL and L/D of a wave cancellation biplanes with AoAD=0°， a wave cancellation biplane with AoAD=3°， a diamond airfoil， and a pair of diamond airfoils

Fig.4

Flow field pressure contour maps for two diamond airfoils at Ma=3， AoA=3°

Fig.5

Flow field around a wave cancellation biplane with a positive AoAD

Fig.6

Comparison of inviscid flow field pressure contour maps at Ma=3， AoA=3° of wave cancellation biplanes with AoAD=0° and AoAD=3°

Fig.7

Supersonic inlet isolator［19］

Table 1

Geometric parameters of supersonic inlet isolator

Fig.8

Mesh for supersonic inlet isolator case

Fig.9

Flow field density contour map of supersonic inlet isolator obtained by CFD

Fig.10

Schlieren image of supersonic inlet isolator［19］

Fig.11

Comparison of supersonic inlet isolator’s wall pressure distributions obtained by CFD and wind tunnel experiment

Fig.12

Pressure and Mach number contour maps of a wave cancellation biplane designed by using the inviscid design method in viscous flow

Fig.13

Geometry of a 3D wave cancellation biplane designed by using the 2D design method

Table 2

Geometric parameters of 3D wave cancellation biplane designed by using 2D design method

Fig.14

Flow field pressure contour maps of 3D wave cancellation biplane designed by using 2D design method

Fig.15

Framework of the optimization design method derived by shock-wave morphology

Fig.16

Schematic diagram of optimization control sections

Fig.17

Automatically generated structural mesh for3D wave cancellation biplane

Fig.18

Extracted flow field information during the optimization process

Fig.19

Flow field pressure contour maps near the throat when the intersection point of the reflected shock wave and the main wing deviates from the throat

Fig.20

Adjustment of geometric parameters

Fig.21

Geometry of optimal configuration with 2 control sections

Table 3

Design Parameters of optimal configuration with 2 control sections

Fig.22

Flow field pressure contour maps of optimal configuration with 2 control sections

Fig.23

Geometry of optimal configuration with 4 control sections

Table 4

Design Parameters of optimal configuration with 4 control sections

Fig.24

Flow field pressure contour maps of the optimal configuration with 4 control sections

Fig.25

Flow field Mach number contour maps of the optimal configuration with 4 control sections

Fig.26

Comparison of lift and drag performance between the original configuration， optimal configurations with 2 control sections and 4 control sections， and a diamond wing

Table 5

Maximum lift⁃to⁃drag ratios and corresponding angles of attack for the four configurations