Accession Number : AD0289681

Title :   HEAT TRANSFER AND PARTICLE TRAJECTORIES IN SOLIDROCKET NOZZLES

Corporate Author : BALLISTIC SYSTEMS DIV NORTON AFB CALIF

Personal Author(s) : TRAVIS,L.P.

Report Date : 19 OCT 1962

Pagination or Media Count : 1

Abstract : Particles present in the exhaust products of solid propellants to which aluminum was added impinge on the walls of the rocket nozzles, transfer heat to the walls, and erode portions of the nozzles. To analyze the effect of impingement, new techniques were developed for calculating three-dimensional particle trajectories and for determining the effects of these particles on heat transfer and erosion in a rocket nozzle. Methods are presented for determining approximate particle trajectories in the subsonic portions of the nozzle by use of an analog computer and for obtaining more accurate digital-computer solutions that can be applied to both the subsonic and supersonic portions. The particle-trajectory studies show that impingement is most severe at the throat region of the nozzle and at the outboard side of the exit cone for multiple-nozzle motors. General equations of motion are presented suggesting nozzle geometries to minimize particle impingement. (Author)

Descriptors :   *ROCKET NOZZLES, EROSION, EXHAUST GASES, GAS FLOW, SOLID ROCKET PROPELLANTS

Distribution Statement : APPROVED FOR PUBLIC RELEASE