Fig.1

Extension from external to internal waverider［10］

Fig.2

Main logic thread

Fig.3

Three kinds of common linear shock waves

Fig.4

Distributions of Crocco and Thomas points’ positions with Mach number［23］

Fig.5

First-order curved shock theory proposed by Mölder［33］

Fig.6

Second-order curved shock theory proposed by Shi et al.［34］

Fig.7

Comparison of original and truncated Busemann basic flowfields［46］

Fig.8

Schematic of ICFC basic flowfield［44］

Fig.9

Schematic of ICFM basic flowfield［55］

Table 1

Comparison of design parameters for various basic flowfields with linear incident shock wave

Fig.10

Comparison of structure for different compression flowfields［56］

Fig.11

Two types of basic flowfields with different pressure distributions

Fig.12

Basic flowfield with non-uniform inflow proposed by Li et al.［71］

Fig.13

Two kinds of basic flowfields with given downstream outlet parameters

Fig.14

Non-axisymmetric internal conical basic flowfield proposed by Zhou et al.［79］

Fig.15

Schematic of streamline tracing technology

Fig.16

HyCAUSE inlet designed in truncated Busemann flowfield［89］

Fig.17

Schematic of Jaws inlet

Fig.18

Schematic of several different multi-modular hypersonic inlets

Fig.19

Schematic of REST inlet design principle

Fig.20

REST inlet optimal design proposed by Xiong et al.［122］

Fig.21

Two typical variable-section design technology for aerodynamic transition

Fig.22

Schematic of viscous correction for inward-turning inlet

Fig.23

Two kinds of hypersonic integration configurations with viscous correction

Fig.24

Starting characteristic judgement curves of hypersonic inlet proposed by Pan et al.［155］

Fig.25

Inlet wall limit streamlines of typical bleeding cases［160］

Fig.26

Using bump to improve inward-turning inlet starting capability［165］

Fig.27

Four kinds of wind tunnel tests for low Mach number starting characteristics

Fig.28

Improving anti-pressure characteristic with vortex generator［194］

Fig.29

Wind tests on anti-pressure characteristic of an inward-turning inlet conducted by He et al.［199］

Fig.30

FaCET project proposed by DARPA

Fig.31

Three-dimensional inward-turning TBCC inlet with twin ducts proposed by Nanjing University of Aeronautics and Astronautics

Fig.32

Three-dimensional inward-turning TBCC inlet with twin ducts proposed by Hu et al.［216］

Fig.33

Three-dimensional inward-turning TBCC inlet with triple ducts proposed by Aerojet［218］

Fig.34

Three-dimensional inward-turning TBCC inlet with triple ducts proposed by Chinese universities

Fig.35

MUTTER inward-turning TBCC inlet with four ducts