THE EXPERIMENTAL EVALUATION OFZ(HYBALINE B3.)Z
Abstract
Hybaline B3 was subjected to 87 test firings in a nominal 100-lb thrust uncooled rocket engine at a chamber pressure of 300 psia. Thirty-seven tests were made with N2O4, 43 with 90 wt % H2O2 and the remainder with 98 wt % H2O2. Twenty-five tests were performed with H2O4 at 500-lb thrust and 1000-psia chamber pressure. Delivered performance with both oxidizers was low in the region of maximum theoretical impulse; however, performance efficiencies significantly increased at weight O/F ratios where combustion temperature was near or above the melting point of beryllium oxide. Thermal stability data are given, as is compatibility information. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1965
- Accession Number
- AD0372023
Entities
People
- Kenneth E. Nidiffer