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The combustion flowfield at the near-injector region of a 50 N scale N 2 O/C 2 H 5 OH thruster was visualized using shadowgraph technique. The explosive ignition was occurred at the design spray condition, and the expanding combustion gas quenched the flame immediately. Approximately after 83 ms from the initial ignition, the propellant spray was re-ignit ed, and the flame was stabilized after 23 ms elapsed. In the increased oxidizer flow rate condition, the transient pressure at the moment of ignition was smoother than explosive ignition, and the blow dow n phenomenon was not appeared in the same operating sequence. In addition, the flame was stabili zed within 17 ms, and it is caused by improved propellants mixing before ignition.  /    50 N    shadowgraph     .     ,        .    83 ms     ,   23 ms     .        ,             17 ms   .            . Key Words:Combustion Flowfield( ), Visualization(), Nitrous Oxide(), Ethanol()

han'gug cujin gonghag hoeji/han-guk chujin-gong hakoeji

Visualization of Transient Ignition Flow-field in a 50 N Scale N&lt;sub&gt;2&lt;/sub&gt;O/C&lt;sub&gt;2&lt;/sub&gt;H&lt;sub&gt;5&lt;/sub&gt;OH Thruster