Accession Number:

AD0485277

Title:

EVALUATION OF SHORT-DURATION ROCKET ENGINE TECHNIQUE FOR BASE HEAT TESTING WITH EXTERNAL AIRFLOW

Descriptive Note:

Technical rept.

Corporate Author:

ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN

Personal Author(s):

• Dawson, Jr, John G.

Report Date:

1966-07-01

Pagination or Media Count:

92.0

Abstract:

Base recirculation data were obtained on a 5.47--scale model of the Saturn 1-Block 2 booster at trajectory Mach numbers of 1.16 and 1.63. The rocket nozzle flow was produced by use of the short-duration combustor. The turbine exhaust gases were simulated by hydrogen. The test objectives were 1 to compare results obtained by the short-duration technique to those obtained by long-duration test methods and 2 to evaluate the operational advantages of the short-duration method as compared to other techniques. A comparison of model test to flight test data is also presented.

Descriptors:

• *BASE FLOW
• *LAUNCH VEHICLES
• *LIQUID PROPELLANT ROCKET ENGINES
• ASCENT TRAJECTORIES
• BASE PRESSURE
• COMBUSTION CHAMBERS
• CONVECTION(HEAT TRANSFER)
• EXHAUST GASES
• EXPERIMENTAL DATA
• HEAT SHIELDS
• HEAT TRANSFER
• HIGH ALTITUDE
• HYDROGEN
• MODEL TESTS
• NOZZLE GAS FLOW
• PERFORMANCE(ENGINEERING)
• PRESSURE
• SUPERSONIC CHARACTERISTICS
• TEST EQUIPMENT
• TEST METHODS
• TIME
• WIND TUNNEL MODELS

Subject Categories:

• Test Facilities, Equipment and Methods
• Fluid Mechanics
• Liquid Propellant Rocket Engines
• Ground Support Systems and Facilities for Space Vehicles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE