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Experimental thrust performance of a high area-ratio rocket nozzleAn experimental investigation was conducted to determine the thrust performance attainable from high-area-ratio rocket nozzles. A modified Rao-contoured nozzle with an expansion area of 1030 was test fired with hydrogen-oxygen propellants at altitude conditions. The nozzle was also tested as a truncated nozzle, at an expansion area ratio of 428. Thrust coefficient and thrust coefficient efficiency values are presented for each configuration at various propellant mixture ratios (oxygen/fuel). Several procedural techniques were developed permitting improved measurement of nozzle performance. The more significant of these were correcting the thrust for the aneroid effects, determining the effective chamber pressure, and referencing differential pressure transducers to a vacuum reference tank.
Document ID
19870014376
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Pavli, A. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Kacynski, K. J.
(NASA Lewis Research Center Cleveland, OH, United States)
Smith, T. A.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 13, 2013
Publication Date
October 1, 1986
Publication Information
Publication: Johns Hopkins Univ., The 23rd JANNAF Combustion Meeting, Volume 1
Subject Category
Spacecraft Propulsion And Power
Accession Number
87N23809
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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