PRELIMINARY STUDY OF AIR AUGMENTATION OF ROCKET THRUST,
Abstract
Assumptions, method of analysis, and results of a paramtric study of thrust augmentation of a fuel-rich rocket by air injection and supersonic afterburning are described. The analysis indicates that significant gains in Isp should be possible. For the 45 per cent aluminum propellant, 1000 psia chamber pressure, and the Mach 3, 40,000-ft flight conditions assumed, the following effects are indicated. The air injection static pressure should be near 50 psia, if possible. High diffuser kinetic energy efficiency is important, but not crucial. Complete mixing is desirable but not crucial. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1964
- Accession Number
- AD0451695
Entities
People
- G. L. Dugger
- R. E. Walker
- R. L. Perini
Organizations
- Johns Hopkins University