Accession Number:

AD0829823

Title:

PRESENTATION OF TEMPERATURE DATA FROM THE HOT ROCKET JET EFFECTS TEST IN THE NACA LEWIS FLIGHT PROPULSION LABORATORY 8 FEET BY 6 FEET WIND TUNNEL,

Descriptive Note:

Corporate Author:

GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA

Personal Author(s):

Report Date:

1958-08-18

Pagination or Media Count:

23.0

Abstract:

Because reliable methods of predicting conditions in the base region of multiple-rocket-powered missiles are non-existent, a wind tunnel test, with a model including hot rockets, was proposed. The main objective of the test was to compare various sustainer turbine exhaust configurations proposed for use on the three-engine missile. Temperature data have been grouped in Table I in a manner which facilitates comparision of the sustainer turbine exhaust configurations.

Subject Categories:

  • Surface-Launched Guided Missiles
  • Rocket Engines
  • Liquid Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE