AN INVESTIGATION OF BASE HEATING ON A 5.47-PER-CENT SCALE MODEL OF THE SATURN S-1 BOOSTER AT TRANSONIC MACH NUMBERS
Abstract
An investigation was conducted in the 16-ft transonic tunnel of the propulsion wind tunnel facility at the Arnold Center to evaluate base heating of the Saturn S-1 booster. Various turbine exhaust stack configurations were tested over a Mach number range of 0.6 to 1.5, an altitude range of 10,000 ft to 42,000 ft, and a missile angle-of-attack range of 0 to -7 1/2 deg. Rocket engines using liquid oxygen and RP-1 were used to simulate the full-scale engine exhaust, and hydrogen was used to simulate the turbo-pump exhaust. Base burning at all test conditions was eliminated for only one of the turbine exhaust stack configurations. Various degrees of base burning were obtained for all other exhaust stack configurations, but no burning occurred at a free-stream Mach number of 1.5 for the trajectory altitude. At altitudes above 29,000 ft, only localized base burning occurred and the accompanying heating rates were low.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1961
- Accession Number
- AD0262743
Entities
People
- J. F. Lowry
- T. L. Kennedy
Organizations
- Arnold Engineering Development Complex