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Applicability of empirical data currently used in predicting solid propellant exhaust plumesTheoretical and experimental approaches to exhaust plume analysis are compared. A two-phase model is extended to include treatment of reacting gas chemistry, and thermodynamical modeling of the gaseous phase of the flow field is considered. The applicability of empirical data currently available to define particle drag coefficients, heat transfer coefficients, mean particle size, and particle size distributions is investigated. Experimental and analytical comparisons are presented for subscale solid rocket motors operating at three altitudes with attention to pitot total pressure and stagnation point heating rate measurements. The mathematical treatment input requirements are explained. The two-phase flow field solution adequately predicts gasdynamic properties in the inviscid portion of two-phase exhaust plumes. It is found that prediction of exhaust plume gas pressures requires an adequate model of flow field dynamics.
Document ID
19780034363
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tevepaugh, J. A.
(Lockheed Missiles and Space Co. Huntsville, AL, United States)
Smith, S. D.
(Lockheed Missiles and Space Co. Huntsville, AL, United States)
Penny, M. M.
(Lockheed Missiles and Space Co., Inc. Huntsville, Ala., United States)
Greenwood, T.
(NASA Marshall Space Flight Center Huntsville, Ala., United States)
Roberts, B. B.
(NASA Johnson Space Center Houston, Tex., United States)
Date Acquired
August 9, 2013
Publication Date
September 1, 1977
Subject Category
Spacecraft Propulsion And Power
Accession Number
78A18272
Distribution Limits
Public
Copyright
Other

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