Rocket Exhaust Flow in Tube Launchers
Abstract
The present investigation, which was primarily of an experimental nature, was undertaken to define the flow field produced when an underexpanded jet is exhausted from a conical nozzle (Rocket exhaust) into a cylindrical tube (tube launcher). The experimental data included the reservoir conditions for the nozzle, the static pressure distribution along the cylinder wall, pilot probe surveys at the cylinder exit, and photographs of the flow exhausting from the tube. Of principal concern were the effects on the flow-field of tube length, of reservoir conditions, and of test time. Although room-temperature nitrogen was used as the test gas in most of the tests, several tests used actual rockets statically fired into the same cylindrical tubes. The experimentally determined flow field characteristics were compared with the experimental data of others, with a method of characteristics analysis developed for the present investigation, and with the flow field model of Fabri and Siestrunck. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 19, 1976
- Accession Number
- ADA035051
Entities
People
- James L. Batson