Heat transfer characteristics of H2/O2-combustion chambers
- 28 June 1993
- conference paper
- conference paper
- Published by American Institute of Aeronautics and Astronautics (AIAA)
Abstract
No abstract availableThis publication has 6 references indexed in Scilit:
- Numerical analysis of high aspect ratio cooling passage flow and heat transferPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1993
- An experimental investigation of high-aspect-ratio cooling passagesPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1992
- Three-dimensional flow analysis in a rocket engine coolant channel of high depth/width ratioPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1991
- Subscale LOX/hydrogen testing with a modular chamber and a swirl coaxial injectorPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1991
- Test results with a regeneratively cooled LOX/LH2 thrust chamber forthe Ariane 3rd stage propulsion systemPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1975
- Space Shuttle Orbiter engine main combustion chamber cooling and lifePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1973