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.
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
1958
23 pages
Report
Keine Angabe
Englisch
Missile Technology , Rocket Propellants , Rocket Engines & Motors , Surface to surface missiles , Sustainer engines , Rocket nozzles , Guided missile models , Wind tunnel models , Temperature , Liquid propellant rocket engines , Heat shields , Configuration , Simulation , Thermal analysis , Hydrogen , Correlation techniques , Instrumentation , Aerodynamic loading
Propulsion wind tunnel at NACA Lewis Laboratory
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