COMBUSTION INSTABILITY IN LIQUID PROPELLANT ROCKET MOTORS
PRINCETON UNIV N J
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Starting problems involving the loss of flame from the solid propellant ignitor have caused three explosions on the 500-lb. thrust tests tangentially oriented 1.4 spuds. The flame holding effect of the solid propellant ignitor is very critical with this injector despite the starting mixture of H-O. The variable-length sector motor was used over a wide range of mixture ratios and lengths. No instability was observed. Nozzle conditions in the longitudinal testing limited the regions of instability. EFfects of variable sector angle above 180 degrees were investigated using iso-octane as a check against the alcohol-liquid O results. Angles above 180 degrees definitely introduce error. The interaction index varies markedly with mixture ratio for iso-octane.