Methane Heat Transfer Characterization For Regenerative- or Convectively-cooled Liquid Rocket Engine Applications
- Paper number
IAC-07-C4.3.04
- Author
Mr. Scott Forde, Aerojet, United States
- Coauthor
Mr. Igor Smirnov, Russia
- Year
2007
- Abstract
This paper discusses the CMDB-Aerojet cooperative project that compiled data on the fundamental heat transfer characteristics of liquid and gaseous methane. The project consisted of collecting and documenting available data, and conducting an experimental test program to fill gaps in existing data. Heat transfer characteristics of methane in the subcritical liquid and gaseous conditions, as well as at supercritical conditions were evaluated, representing engines operating over a range of chamber pressures from 8 to 210 bar. Test conditions included coolant inlet pressure levels from 10 to 250 kg/cm2, with inlet temperatures ranging from 110 to 300ºK. Data collected included inlet and outlet bulk temperatures, local wall temperatures, coolant velocities, and heat fluxes. The results of the testing were correlated to a coolant side film coefficient as a function of the methane Reynolds and Prandtl numbers in the test section. The test results now form a database available for design of regeneratively-cooled or convectively-cooled rocket engine thrust chambers.
- Abstract document
- Manuscript document
IAC-07-C4.3.04.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.