Injection and Combustion of Hypergolic Propellants. Part 1. Reactive Stream Impingement. Part 2. Extension of Steady-State Combustion Model
Abstract
Mixing and separation criteria of hypergolic propellants are characterized by a chemical reaction time and a mixing time. Separation limit is defined by assuming the two characteristic times to be equal. Experimental results with hydrazine and nitrogen tetroxide propellants agree very well with this separation limit, and also show that the effect of chamber pressure is not significant. MMH and A-50 with nitrogen tetroxide give separation limits at higher propellant temperatures. It appears that stream separation always occurs by impinging compound A and hydrazine with oxidized and fuel temperatures varying between 0F to 30F and 40F to 60F. A second work area of the project was concerned with the extension of the Steady-State Combustion Computer Model. The computer program was generalized to allow increased versatility in running various propellant systems. The numerical procedures and organizations of the program were substantially improved. Propellant property values were gathered for several systems of current interest. A computer program listing is presented.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1969
- Accession Number
- AD0853233
Entities
People
- B. P. Breen
- B. R. Lawver
- D. E. Coats
- L. B. Zung
- T. C. Kosvic