Accession Number : ADA017713
Title : The Analysis of the Launch-Tube Flow-Field for Arrow Firings,
Corporate Author : TEXAS UNIV AT AUSTIN DEPT OF AEROSPACE ENGINEERING AND ENGINEERING MECHANICS
Personal Author(s) : Bertin,John J. ; Galanski,Stanley R.
Report Date : MAY 1975
Pagination or Media Count : 51
Abstract : The present report discusses launcher flow-field data from launchings of the Arrow configuration, which were conducted at the U.S. Army Missile Command facility in Huntsville, Alabama. The experimental static-pressure-distributions obtained in the Arrow launch tube indicate that the exhaust flow was fully supersonic both in the forward tube and in the aft tube. The correlation between the data and the values calculated using a crude theoretical model indicate that the flow could pass through the Arrow constriction without generating a normal shock wave. These results are in marked contrast to the results of the Rip-Zap test program where the flow was choked by the constriction and a normal shock wave was produced. Analysis of the data from the programs conducted to date has demonstrated that the flow field in the launcher depends on the ratio of the nozzle-exit radius: aft-tube radius: forward-tube radius, the mass-flow-rate of the exhaust flow and the impingement shock-wave generated when the exhaust flow encounters the launcher wall.
Descriptors : *Interior ballistics, *Launch tubes, *Flow fields, *Rocket launchers, *Artillery rockets, Cross sections, Free flight trajectories, Rocket exhaust, Supersonic flow, Shock waves, High temperature, Back pressure, Walls, Static pressure, Flight testing
Subject Categories : Rockets
Distribution Statement : APPROVED FOR PUBLIC RELEASE