SHOCK-WAVE PROPAGATION IN LIQUID PROPELLANT ROCKET ENGINES

A model is presented for longitudinal shock-wave propagation in liquid propellant rocket engines. The equations, which include the effects of gaseous dissociation, contain appropriate terms to account for the drag, possible shattering, evaporation, and subsequent combustion of the liquid fuel drops....

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Bibliographic Details
Main Authors: AGOSTA,Vito D, Chinitz,Wallace
Format: Report
Language:English
Subjects:
COMBUSTION
COMBUSTION CHAMBERS
DRAG
DROPS
EQUATIONS
JET ENGINE FUELS
JP-5 FUEL
LIQUID PROPELLANT ROCKET ENGINES
LIQUID ROCKET PROPELLANTS
PROPAGATION
SHOCK WAVES
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Summary:A model is presented for longitudinal shock-wave propagation in liquid propellant rocket engines. The equations, which include the effects of gaseous dissociation, contain appropriate terms to account for the drag, possible shattering, evaporation, and subsequent combustion of the liquid fuel drops. The equations are solved numerically on a digital computer. A comparison of the results obtained with previous experimental work performed in a shock tube indicates good agreement for shock-wave pressure ratios above about 3.5. (Author) Pub. in Pyrodynamics v1 p299-317 1964(Copies available only to DDC users). Prepared in cooperation with General Applied Science Labs., Inc., N. Y. Presented at the National Meeting of the American Institute of Chemical Engineers (49th) New Orleans, March 1963.