Date of Award
12-1995
Document Type
Thesis
Degree Name
Master of Science
Department
Department of Aeronautics and Astronautics
First Advisor
Jerry Bowman, PhD
Abstract
This study proved that transpiration cooling provides a better cooling scheme than regenerative cooling for long operating duration, liquid-fueled rocket engine nozzles. This proof was made on the basis of maximum wall temperature. This study compared transpiration cooling to regenerative cooling in the throat region of the Space Shuttle Main Engine Main Combustion Chamber. The study also analyzed the effects of porosity, solid thermal conductivity, and porous sphere size on a porous wall made of packed spheres. The transpiration cooled nozzle operated 35% cooler than a regeneratively cooled nozzle, but the temperature gradient at the hot gas surface was 72 times greater than the regeneratively cooled nozzle.
AFIT Designator
AFIT-GA-ENY-95D-01
DTIC Accession Number
ADA303221
Recommended Citation
Landis, Jay A., "Numerical Study of a Transpiration Cooled Rocket Nozzle" (1995). Theses and Dissertations. 6118.
https://scholar.afit.edu/etd/6118