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,
GENERAL DYNAMICS/ASTRONAUTICS SAN DIEGO CA
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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.
- Surface-Launched Guided Missiles
- Rocket Engines
- Liquid Rocket Propellants