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This chapter contains methods and procedures for determining plume induced based flowfields and heating environments. State-of-the-art techniques for determining base flow conditions are presented for missiles and launch vehicles with a single propulsive engine as well as a variety of multiple base configurations. The methodology spans the complete spectrum of external flow conditions from the launch phase through powered flight at supersonic and hypersonic conditions, and includes plume backflow impingement from motors operated at near vacuum conditions. Propulsion engines utilizing liquid and solid propellants are considered. (Author).
The JANNAF Rocket Exhaust Plume Technology Handbook was prepared with the objectives of bringing into one document the major principles, formulae, and facts concerning exhaust plume technology. The handbook is being published in loose leaf form so that chapters dealing with the various aspects of plume technology can be incorporated as they are completed and approved for publication. The handbook is intended for the use of workers in the field of rocket exhaust plume technology. It is not meant to be an extensive state-of-the-art review but rather to be a document which stresses the solution to common everyday plume problems.
THIS HANDBOOK DESCRIBES THE THEORY AND APPLICATION OF QUANTITATIVE TECHNIQUES FOR PREDICTING ROCKET PLUME RADIATION. The work has primarily been in the area of the shortwave infrared (SWIR) because rocket exhaust gases are typically at temperatures on the order of 2000 to 2500 K, for which the Planck blackbody spectral distribution peaks in the SWIR. Another reason for this is that IR sensor technology is highly developed in the SWIR. In addition, the SWIR is dominated by vibration-rotation molecular emission bands of major species in the plumes.
This volume, the first of three volumes, is a collection of 10 unclassified/unlimited papers which were presented at the 21st Joint Army-Navy-NASA-Air Force (JANNAF) Exhaust Plume Technology Subcommittee Meeting in conjunction with the Combustion Subcommittee and SPIRITS User Group Meeting held 19-21 October 1994 at the Lockheed Missiles and Space Company, Sunnyvale, California. Specific subjects discussed include behavior of aluminum and aluminum oxide in solid rocket plumes, exhaust plume flowfield characterization and plume phenomena at high altitudes.
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.