A computer model of external burning propulsion of axisymmetric, supersonic vehicles is described. Reactive gaseous injectant issues from individual nozzles around the vehicle periphery, near the base. At the base these individual jets merge into an annulus of injectant surrounding the base cavity. Detailed individual-jet calculations in the region upstream of the base are made by an existing analysis developed for fuel-rich jet interaction. The injectant annulus is calculated assuming an adjustable fraction of the flow at equilibrium and the remainder frozen; mass and momentum are conserved, and the transverse pressure gradients are assumed negligible. Results and trends are presented for parameters including Mach number, altitude, vehicle geometry and injectant mass and momentum flux and composition. (Author)
An Analysis of External Burning Propulsion
1979
83 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , External burning , Propulsion systems , Computerized simulation , Supersonic combustion , Supersonic flight , Base pressure , Systems engineering , Injectors , Liquids , Gases , Projectiles , Rocket engines , Exhaust gases , Solid rocket propellants , Fuels , Bipropellants , Solid propellants , Mathematical models
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