Accession Number:

AD0829814

Title:

DETERMINATION OF PROPELLANT RECIRCULATION ON A 1/30 SCALE ATLAS MODEL USING RARE GAS TRACER TECHNIQUES,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s):

Report Date:

1958-08-14

Pagination or Media Count:

23.0

Abstract:

A 130 scale model of the Atlas missile was tested in the NACA Wind Tunnel to study the characteristics of recirculation and heating by fuel-rich rocket and turbine exhaust gases burning in the vicinity of the blunt aft section of the missile. A method to determine the relative contributions from these gaseous sources was devised based on the sampling and analysis of tracer gases added to the propellants. One percent helium and one percent neon, respectively, were added to the rocket and turbine gases. Naturally occurring air contains about one percent argon. Samples from the base region were withdrawn through a set of tubes during the rocket firingg. The proportions of helium, neon and argon were determined with a mass spectrometer, and from these proportions by weight of rocket propellant, turbine exhaust, and air at the point of sampling were calculated. Thus, the presence and source of a mixture with potential heating value in the base region was determined. Author

Subject Categories:

  • Guided Missile Dynamics, Configurations and Control Surfaces
  • Surface-Launched Guided Missiles
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE