The objective of this research is to determine some of the design criteria and the expected performance of the combustor and nozzle for hypersonic ramjets with supersonic combustion of hydrogen in the flight Mach number range from 5 to at least 10. (Author)
Research and Exploratory Development for the Office of Aeronautical Research, National Aeronautics and Space Administration
1968
13 pages
Report
Keine Angabe
Englisch