DETERMINATION OF ROCKET EXHAUST GAS TEMPERATURES AND EMISSIVITIES BY INFRARED SPECTRAL METHODS. SIMULATED HIGH ALTITUDE TESTS OF A SCALE MODEL ROCKET ENGINE
Abstract
To supplement laboratory studies of infrared radiance of flames, infrared spectral emittance and absorptance of the exhaust plume of a Hydrogen-Oxygen rocket engine were measured. The engine, a tenth-scale model of the Saturn-IV, was fired in an altitude test chamber, under conditions simulating altitudes from 96,000 to 145,000 feet. Exhaust gas temperatures and emissivities were determined from the infrared spectral measurements. Laboratory measurements of hydrogen-oxygen flame emissivities were extrapolated to the case of the test rocket engine. The measured results verified the extrapolation, within the range of error determined by experiment and the limitations of the extrapolation procedure. It is concluded that the results support the extrapolation from laboratory flame measurements, and that refinement of both theory and experiment are required, to improve accuracy. The tests also demonstrated the utility of the IMRA infrared technique and instrumentation for measuring gas temperatures in rocket engines. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 01, 1961
- Accession Number
- AD0271673
Entities
People
- Gunter J. Penzias
- Richard H. Tourin
- Stanley A. Dolin