Effect of fueling scheme on scramjet combustion performance was investigated based on pulse wind-tunnel direct connected experiment platform. Both pressure measurement and high speed videos were employed.The time evolution of flame with ethylene injected at different single injectors was demonstrated by high speed videos.Under the limits of producing effective thrust and avoiding inlet un-start

the first and second injectors' least and largest fuel equivalence ratios(ER) for combustion were obtained from injecting characteristics experiments.The coupling of the first and second injectors with others was studied.With these initiatory results gained above

different fueling schemes for best combustion performance were investigated under three indexes:isolator undisturbed length

combustor inner thrust and fuel specific impulse.The optimum values for these three indexes were 149.6mm

1622.3N and 1354.0s separately.