Fig.1

Ground direct-connected experimental system for powder enhanced scramjet

Fig.2

Geometric parameter of powder enhanced scramjet

Table 1

High enthalpy incoming flow parameters

Fig.3

Schematic diagram of direct-connected scramjet measurement system

Fig.4

Thrust bench guide friction calibration

Fig.5

Results of in situ calibration of engine thrust

Fig.6

Magnesium powder for scramjet experiments

Table 2

Experimental conditions for powder enhanced scramjet

Fig.7

Composition of thrust in a scramjet

Fig.8

Principle of total pressure measurement at combustor outlet

Fig.9

Combustion chamber pressure distribution： RP-3 vs RP-3+5% SiO2

Fig.10

Typical PES test sequence and variation of engine exhaust plume

Fig.11

Spectral characteristic curves of engine exhaust plume

Fig.12

Typical PES thrust measurement results

Fig.13

Engine thrust with kerosene injection only

Fig.14

Injection pressure of gas-solid two-phase flow during the test

Fig.15

Reproducibility validation of engine test results

Fig.16

Combustion chamber pressure distribution： ER 1.0 vs ER 1.3

Table 3

Thrust performance parameters

Fig.17

Combustion chamber pressure distribution under different powder-gas mass flow ratios

Fig.18

Specific impulse performance under different powder-gas mass flow ratios

Table 4

Mach number of combustor outlet

Fig.19

Static temperature of combustor outlet and combustion efficiency

Fig.20

Deposition of condensate products in powder injection section

Table 5

Specific impulse of PES

Fig.21

Combustor pressure distribution along axis under different injection positions

Fig.22

Relationship between powder residence distance and thrust performance

Fig.23

Thermogravimetric analysis of magnesium powder

Fig.24

Combustion products of magnesium powder in carbon dioxide， water vapor， and mixedatmospheres

Fig.25

X-ray diffraction analysis of condensed phase deposition at combustor outlet

Fig.26

Microstructure and element distribution of condensed phase products