- Author
- Zung, L. B. | White, J. R.
- Title
- Combustion Process of Impinging Hypergolic Propellants.
- Coporate
- Marshall Industries, Irvine, CA
- Sponsor
- National Aeronautics and Space Administration, Lewis Research Center, Cleveland, OH
- Report
- NASA CR-1704; SN-145-F, May 1971, 43 p.
- Contract
- NAS-3-12031
- Keywords
- hypergolic rocket propellants | combustion | atmospheric pressure | mixing | pressure | combustion chambers
- Identifiers
- stream separation; combustion popping; liquid mixing
- Abstract
- Single exposure photography and high speed motion pictures were used to study the sprays formed by impinging streams of liquid hydrazine and nitrogen tetroxide. Chamber pressures were varied between 15 Psia and 500 Psia. Four different orifices (.027" to .060") were used. Propellant temperatures and velocities were varied from 40 deg F to 140 deg F and 15 ft/sec to 95 ft/sec, respectively. Influence of chamber pressure and propellant temperature on separation and mixing were determined. Effects of orifice diameter and chamber pressure on the occurrence of popping were quantitatively evaluated.