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Propellant vaporization as a criterion for rocket engine design ; relation between percentage of propellant vaporized and engine performance
- Author / Creator
- Available as
- Online
- Summary
-
An analysis is presented on the quantitative effect of incomplete propellant vaporization on rocket-engine performance. A relation between characteristic exhaust velocity c* and the percentages of ...
An analysis is presented on the quantitative effect of incomplete propellant vaporization on rocket-engine performance. A relation between characteristic exhaust velocity c* and the percentages of oxidant and fuel vaporized and burned is given. The analysis shows that c* efficiencies of 70 to 90 percent can be realized when only half the fuel is vaporized, whereas c* efficiencies of about 60 percent can be realized when half the oxidant is vaporized. The specific relations between c* and propellant vaporized are presented graphically for the hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine, and JP-4 - oxygen propellant combinations. The analysis is applied to experimental data for these propellant combinations.
Details
- Creator
- by Marcus F. Heidmann and Richard J. Priem
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington : National Advisory Committee for Aeronautics, 1958
- Physical Details
-
- 1 online resource (19 pages) : illustrations
- data file
- OCLC
- on1440237478
- Date of issue: March 1958.
- Report numbers NACA-TN-4219.
- "Lewis Flight Propulsion Laboratory."
- Title from title screen (viewed June, 4, 2024)
- Includes bibliographical references (page 7)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.