[PDF] Influence Of Chemical Kinetic And Turbulent Transport Coefficients On Afterburning Rocket Exhaust Plume Properties eBook

Author : H. S. Pergament
Publisher :
Page : 28 pages
File Size : 12,18 MB
Release : 1970
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The influence of chemical kinetic and turbulent transport coefficients on afterburning rocket exhaust plume properties was analyzed in terms of predicted radar attenuations transverse to solid propellant plumes. A model of parallel turbulent mixing and nonequilibrium combustion and ionization was used to determine whether varying these coefficients, which are input data to the model, over their ranges of uncertainty has a significant effect on the predicted attenuation. The results of the study demonstrate that significant differences in predicted attenuation levels can result when the important reaction rate and turbulent transport coefficients are varied within their respective error bounds. This establishes the framework within which to interpret radar attenuation data taken at sea level and under simulated altitude conditions. It is also shown that a better laboratory determination of the rate coefficient for the dominant charge-producing reaction, K + Cl yielding K(+) + Cl( - ), is of particular importance if more accurate attenuation predictions are to be made. It was concluded that realistic calculations of solid propellant exhaust plume electrical properties must take chemical kinetics into account. (Author).

Author :
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Page : 13 pages
File Size : 17,16 MB
Release : 1976
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A review of the accomplishments achieved under this AFOSR contract is presented. Among the most notable are: (1) the development and demonstration of a fully-coupled rocket nozzle code (FULLNOZ) which, in calculating nozzle flow properties, couples the effects of nonequilibrium chemistry, gas/particle thermal and dynamic nonequilibrium, turbulent mixing across streamtubes and turbulent wall boundary layers and (2) the development of a phenomeno-logical model for the interpretation of IR radiation data from subscale liquid propellant rocket motor plumes; the model accounts for the effects of unburned fuel on rocket nozzle and after-burning plume properties.

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Publisher :
Page : 190 pages
File Size : 12,7 MB
Release : 1990
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Describes experimental work performed on a high-speed pre-mixed hydrogen-air jet flame in a co-flowing annular air flow in the presence and absence of base flow at the exit. Includes details on the high-speed flame in a coaxial air facility which was designed, built, and tested to simulate (in a first approximation) rocket exhaust flow conditions. In addition, a new high spatial resolution computer-controlled three-dimensional gear was built to traverse the investigated flow field. The main experimental tool was a two-dimensional laser Doppler velocimeter with data acquisition and processing system. The tool was used to measure the two main velocity components. Other measurements included turbulence intensities and mean temperatures at various downstream sections. The measured initial and flow field data will serve to evaluate the validity of various turbulence models and to predict the structure of rocket exhaust plumes. Moreover, the experiments established the effect of the base flow on the turbulence structure of the exhaust plume.

Author : Frederick S. Simmons
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 312 pages
File Size : 39,65 MB
Release : 2000
Category : Science
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This new book deals with the phenomenology of rocket exhaust plumes as the targets of space-based surveillance systems. Topics include the physical and chemical processes in rocket engines and their exhaust plumes, particularly in regard to flow properties, gas dynamics, and radiative mechanisms that are responsible for the generation of emission in rocket exhaust plumes at infrared and other wavelengths. System designers in a number of defense-related areas will be able to put the information in this book to immediate use.