Accession Number : AD0451695


Title :   PRELIMINARY STUDY OF AIR AUGMENTATION OF ROCKET THRUST,


Corporate Author : JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB


Personal Author(s) : Perini, R L ; Walker, R E ; Dugger, G L


Report Date : Jan 1964


Pagination or Media Count : 23


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)


Descriptors :   *SOLID PROPELLANT ROCKET ENGINES , *THRUST , THRUST AUGMENTOR NOZZLES , AIR , PRESSURE , DENSITY , INTERIOR BALLISTICS , DIFFUSION , INJECTION , SPECIFIC IMPULSE , REACTION KINETICS , NOZZLE GAS FLOW , COMBUSTION , SOLID ROCKET PROPELLANTS


Distribution Statement : APPROVED FOR PUBLIC RELEASE