Accession Number:

AD0483640

Title:

EVALUATION OF AN UNCOOLED ROCKET ENGINE OPERATING TECHNIQUE APPLICABLE TO THE EXPERIMENTAL STUDY OF MISSILE BASE HEATING

Descriptive Note:

Technical rept. 29 Nov-6 Dec 1965

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Parker, J. R.
• Christenson, R. J.

Report Date:

1966-06-01

Pagination or Media Count:

90.0

Abstract:

A description is given of an uncooled rocket engine operating technique applicable to the experimental study of missile base heating. The primary advantage offered by this technique over those in current use is that it retains the single combustion chamber, uncooled engine concept of the short- duration test technique while providing burn durations of sufficient time to permit use of conventional, steady-state instrumentation. This technique also eliminates the usually complex propellant and control systems associated with conventional liquid-cooled long-duration engines. Uncooled engine operating characteristics are reported for burn durations of 1.2 sec extrapolation of these data indicate engine burn duration can be extended to 2.5 sec. Base heating data obtained with a 5.47-scale Saturn I-Block II model utilizing the uncooled engine test technique are compared with data from a Saturn I-Block II model which utilized short- and long-duration test techniques.

Descriptors:

• *GUIDED MISSILES
• *LIQUID PROPELLANT ROCKET ENGINES
• *ROCKET ENGINES
• BASE FLOW
• BASE PRESSURE
• BURNING RATE
• COMBUSTION CHAMBERS
• COPPER
• FLUID FLOW
• FUEL INJECTORS
• FUEL SYSTEMS
• HEAT FLUX
• HEAT TRANSFER
• HEATING
• INTERIOR BALLISTICS
• LAUNCH VEHICLES
• NOZZLE CLUSTERS
• ROCKET NOZZLES
• SHIELDING
• TANTALUM
• TUNGSTEN
• TUNGSTEN ALLOYS
• VENTURI TUBES

Subject Categories:

• Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE