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naca-tn-4219

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National Advisory Committee for Aeronautics, Technical Notes - Propellant Vaporization as Criterion for Rocket Engine Design; Relation Between Percentage of Propellant Vaporized and Engine Performance

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* effi—
ciencies 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.

Characteristic exhaust velocity is commonly used as an experimental
measure of the completeness of combustion in rocket engines. This param-
eter may indicate inefficiencies in the combustion process that may be
due to incomplete reaction, mixing, propellant vaporization, and other
causes. Reported herein is an analysis relating the characteristic ex-
haust velocity to the percentage of propellant vaporized.

Propellant vaporization is considered in this report as the factor
that limits the rate at which the combustion process proceeds within a
rocket engine. The importance of propellant vaporization is also ems
phazised in references 1 to 5. The analytical studies of references 4
and 5 are based on the hypothesis that the combustion rate is completely
governed by the rate of propellant vaporization. Qualitatively, these
analyses are in agreement with experimental results. Exact comparisons
of experimental and analytical results, hOWever, require further refine-
ments in the interpretation of data. For this purpose, a method of data
analysis has been devised to relate experimental c* data to the per-
centage of propellant vaporized.

The treatment of experimental data reported herein is consistent with
the analytical combustion model used in droplet-vaporization calculations
reported in references 4 and 5. Application of the method of analysis to
the hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine, and JP-é - oxygen
propellant combinations is described.

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naca-tn-4219

  • Version
  • 126 Downloads
  • 766.63 KB File Size
  • 1 File Count
  • February 3, 2017 Create Date
  • February 3, 2017 Last Updated
Scroll for Details

National Advisory Committee for Aeronautics, Technical Notes - Propellant Vaporization as Criterion for Rocket Engine Design; Relation Between Percentage of Propellant Vaporized and Engine Performance

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* effi—
ciencies 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.

Characteristic exhaust velocity is commonly used as an experimental
measure of the completeness of combustion in rocket engines. This param-
eter may indicate inefficiencies in the combustion process that may be
due to incomplete reaction, mixing, propellant vaporization, and other
causes. Reported herein is an analysis relating the characteristic ex-
haust velocity to the percentage of propellant vaporized.

Propellant vaporization is considered in this report as the factor
that limits the rate at which the combustion process proceeds within a
rocket engine. The importance of propellant vaporization is also ems
phazised in references 1 to 5. The analytical studies of references 4
and 5 are based on the hypothesis that the combustion rate is completely
governed by the rate of propellant vaporization. Qualitatively, these
analyses are in agreement with experimental results. Exact comparisons
of experimental and analytical results, hOWever, require further refine-
ments in the interpretation of data. For this purpose, a method of data
analysis has been devised to relate experimental c* data to the per-
centage of propellant vaporized.

The treatment of experimental data reported herein is consistent with
the analytical combustion model used in droplet-vaporization calculations
reported in references 4 and 5. Application of the method of analysis to
the hydrogen-fluorine, hydrogen-oxygen, ammonia-fluorine, and JP-é - oxygen
propellant combinations is described.

FileAction
naca-tn-4219 Propellant Vaporization as Criterion for Rocket Engine Design; Relation Between Percentage of Propellant Vaporized and Engine Performance.pdfDownload 
17,005 Documents in our Technical Library
2449809 Total Downloads

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Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
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ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...