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):
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