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.
Evaluation of Short-Duration Rocket Engine Technique for Base Heat Testing with External Airflow
1966
82 pages
Report
No indication
English
Fluid Mechanics , Space Launch Vehicles & Support Equipment , Rocket Engines & Motors , Laboratory & Test Facility Design & Operation , Launch vehicles , Base flow , Liquid propellant rocket engines , Supersonic characteristics , Heat transfer , Base pressure , Heat shields , Test methods , Time , High altitude , Ascent trajectories , Convection(Heat transfer) , Combustion chambers , Pressure , Hydrogen , Exhaust gases , Nozzle gas flow , Wind tunnel models , Model tests , Performance(Engineering) , Experimental data , Test equipment , Base temperature , Saturn launch vehicles
Engineering Index Backfile | 1960
Engineering Index Backfile | 1960