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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.
The NASA Technical Reports Servcr (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.
The Generalized Implicit Flow Solver (GIES) computer program, developed under sponsorship of the Air Force Phillips Laboratory, Edwards Air Force Base, CA, has been modified and used for three-dimensional reacting two-phase flow problems. The intent of the original GIFS development effort was to provide the JANNAF community with a standard computational methodology to simulate multiple nozzle/plume flow-field phenomena and other three-dimensional effects. Recent development efforts have concentrated on improving the run time and robustness of the algorithm. The GIFS computer program was originally released as an untested research version. Since that time, several corrections and enhancements have been made to the model. The Van Leer Flux Splitting option has been successfully implemented into the existing GIFS model and provides a more robust solution scheme. A Parabolized Navier-Stokes (PNS) version of the GIFS algorithm is currently under development and is intended to substantially improve the run-time requirements for flow fields dominated by supersonic flow regimes. These improvements and enhancements will foster the application of the GIFS model in the CFD community. This paper reports the significant results of several twin-nozzle/plume applications of the GIFS code. Six simulations of Titan II plume flow fields have been completed to assess the effects of three-dimensionality, turbulent viscosity, afterburning, near-field shock structure, finite-rate kinetic chemistry, intranozzle geometric spacing, and initial nozzle exit plane profile effects on the subsequent plume exhaust flow field. The results of these calculations indicate that the viscous stress model, kinetic chemistry, and nozzle exit profile are significant parameters that should be considered in analyses and interpretation of the calculations.
An improved aerodynamic model is proposed for the exhaust plume issuing from a low-altitude rocket nozzle exit into quiescent ambient air in which chemical reactions and compressibility predominate. The model is based on the presently available knowledge and established aerodynamic principles for the various flow regimes involved. The major assumptions made are individually substantiated by related experimental evidence in existing literature. A theoretical analysis is carried over the whole flow region based on the Karman's integral approach to find solutions for the gross aerodynamic and thermodynamic behavior of the plume. Theory incorporating on empirically derived constants provides the required radial distribution function for the integration. Solutions are obtained for the velocity, density, temperature and chemical composition fields for extended regions of the plume. These results will provide the much needed framework for the understanding of the elements which contribute to the phenomenon of radar attenuation of rocket exhaust plumes. (Author).