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,

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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.

Author(s):
Frost, E. E.
Author Organization(s):
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
Pagination:
0023

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
GDA-ZT-7-017-TN
Contract/Grant Number(s):
AF 04(647)-104
 Subject Terms
Joint Capability Areas:
JCA_3.2_Engagement; JCA_3_Force Application; JCA_3.2.1_Kinetic Means
Communities of Interest:
Weapons Technologies
Descriptor(s):
*ROCKET NOZZLES, *SURFACE TO SURFACE MISSILES, SUSTAINER ENGINES, GUIDED MISSILE MODELS, TEMPERATURE, LIQUID PROPELLANT ROCKET ENGINES, HEAT SHIELDS, CONFIGURATIONS, SIMULATION, THERMAL ANALYSIS, HYDROGEN, CORRELATION TECHNIQUES, INSTRUMENTATION
Field(s)/Group(s):
Surface-Launched Guided Missiles, Rocket Engines, Liquid Rocket Propellants
Report Date:
1958 Aug 18