Propellant Vaporization as a Criterion for Rocket Engine Design; Relation Between Percentage of Propellant Vaporized and Engine Performance
Propellant Vaporization as a Criterion for Rocket Engine Design; Relation Between Percentage of Propellant Vaporized and Engine Performance

Author: Marcus F. Heidmann

Publisher:

Published: 1958

Total Pages: 19

ISBN-13:

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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.

Propellant Vaporization as a Criterion for Rocket-engine Design; Calculations of Chamber Length to Vaporize Various Propellants
Propellant Vaporization as a Criterion for Rocket-engine Design; Calculations of Chamber Length to Vaporize Various Propellants

Author: Richard J. Priem

Publisher:

Published: 1958

Total Pages: 36

ISBN-13:

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Vaporization rates were calculated for drops of n-heptane, ammonia, hydrazine, oxygen, and fluorine. The percent propellant vaporized is correlated with an effective chamber length for various spray conditions, and various engine-design and operating parameters. The results show that the effective chamber length required to vaporize a given high percentage of propellant is the shortest with oxygen and increases for fluorine, heptane, ammonia, and hydrazine in that order.