Accession Number : ADA258459
Title : Projectile Base Bleed Technology. Part 1. Analysis and Results.
Descriptive Note : Final rept. Jul 1988-Jul 1991
Corporate Author : SCIENTIFIC RESEARCH ASSOCIATES INC GLASTONBURY CT
Personal Author(s) : Gibeling, Howard J ; Buggeln, Richard C
Report Date : Nov 1992
Pagination or Media Count : 90
Abstract : Detailed finite rate chemistry models for H2 and H2-CO combustion have been incorporated into a Navier-Stoke computer code and applied to flow field simulation in the base region of an M864 base burning projectile. Results without base injection were obtained using a low Reynolds number k-e. turbulence model and several mixing length turbulence models The results with base injection utilized only the Baldwin-Lomax model for the projectile forebody and the Chow wake mixing model downstream of the projectile-base. A validation calculation was performed for a supersonic hydrogen-air burner using an H2, reaction set which is a subset of the H2-CO reaction set developed for the base combustion modeling. The comparison with the available experimental data was good, and provides a level of validation for the technique and code developed. Projectile base-injection calculations were performed for a flat base M864 projectile at M. - 2. Hot air injection, H2 injection and H2-CO injection were modeled, and computed results show reasonable trends in the base pressure increase (base drag reduction), base corner expansion and downstream wake closure location.
Descriptors : *PROJECTILES , *COMBUSTION , COMPUTER PROGRAMS , SIMULATION , INJECTION , CLOSURES , RATES , CARBON , HYDROGEN , CHEMISTRY , DRAG , NUMBERS , CARBON MONOXIDE , EXPANSION , MIXING , WAKE , PRESSURE , LENGTH , FLOW FIELDS , MONOXIDES , DRAG REDUCTION , BASE FLOW , BASE PRESSURE , BURNERS , REYNOLDS NUMBER , REDUCTION , REGIONS , TURBULENCE , COMPARISON , EXPERIMENTAL DATA , VALIDATION , COMPUTERS
Subject Categories : Ammunition and Explosives
Combustion and Ignition
Distribution Statement : APPROVED FOR PUBLIC RELEASE