An Investigation of Base Heating with a 5.47-Percent Saturn SA-1 Booster Model at Mach Numbers 0.8 and 1.15
Abstract
An investigation was conducted to determine the base recirculation characteristics of the simulated propellant pump turbine exhaust gases of a 5. 47-% scale model of the SA-1 Saturn afterbody. Gaseous hydrogen was used to simulate the combustible turbine exhaust gas of the fullscale missile. Base heating and pressure data were obtained at simulated flight trajectory conditions of M=0.8 0.8(16,000-ft) and M=1.15 1.15(27,500-ft) using several turbine exhaust duct configurations. In addition, the effect on base heating with one engine inoperative, of variation in turbine exhaust gas momen um, of finned-model operation, of variation in engine O/F ratio, and of variation in altitude was investigated. At both simulated flight trajectory conditions, the lowest base heating rates were obtained using a streamlined turbine exhaust duct configuration. The following conditions reduced base heating, based on data obtained with the long turbine exhaust ducts: operation with one engine inoperative, increased turbine exhaust gas discharge momentum, and increased engine O/F ratio.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1961
- Accession Number
- AD0266234
Entities
People
- Joseph R. Parker Jr.
- T. J. Gillard
Organizations
- Arnold Engineering Development Complex