An analytical and experimental investigation was conducted to develop an understanding of the mechanisms that cause reactive stream separation, commonly called blowapart, for hypergolic propellants. The investigation was limited to a N2O4/MMH propellant combination and to a range of engine-operating conditions applicable to the space tug and space shuttle attitude control and orbital maneuvering engines. Primary test variables were: chamber pressure (1 to 20 atm), fuel injection temperature (283 to 400 K)m and propellant injection velocity (9 to 50 m/s). The injector configuration studied was the unlike doublet. The reactive stream separation experiments were conducted using special combustors designed to permit photography of the near-injector spray combustion flow field. Analysis of color motion pictures provided the means of determining the occurrence of reactive stream separation.
High performance N2O4/amine elements
1976-03-01
Report
Keine Angabe
Englisch
High Performance N2O4/Amine Elements
NTIS | 1976
|High Performance N2O4/Amine Elements
NTRS | 1976
|High performance N2O4/amine elements: Blowapart
NTRS | 1977
|High Performance N2O4/Amine Elements: Blowapart
NTIS | 1977
|NTRS | 1986
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