[PDF] The Rocket Exhaust Plume Program Rep 1 eBook

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Rocket Exhaust Plume Phenomenology

Frederick S. Simmons
Rocket Exhaust Plume Phenomenology by Frederick S. Simmons PDF

Author : Frederick S. Simmons
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 312 pages
File Size : 43,21 MB
Release : 2000
Category : Science
ISBN :

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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.

A Fully-Coupled Underexpanded Afterburning Rocket Plume Program (The AIPP Code). Part 1. Analytical and Numerical Techniques

H. S. Pergament
A Fully-Coupled Underexpanded Afterburning Rocket Plume Program (The AIPP Code). Part 1. Analytical and Numerical Techniques by H. S. Pergament PDF

Author : H. S. Pergament
Publisher :
Page : 48 pages
File Size : 18,55 MB
Release : 1974
Category :
ISBN :

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A comprehensive computer code has been developed to determine afterburning rocket plume characteristics over a wide altitude range. The code constitutes a significant advance over previous plume codes because it computes the plume shock structure while simultaneously accounting for turbulent mixing, nonequilibrium chemistry and gas/particle nonequilibrium effects. The capability of calculating properties in the subsonic region downstream of the Mach disc, downstream of the shock reflected from the triple point and in the far field has been incorporated into the code, but has not yet been debugged. This report describes the analytical and numerical techniques incorporated into the code, demonstrates that predictions of inviscid, chemically-frozen plume flows are as accurate as those obtained from a proven method of characteristics code and gives the results of some sample calculations for the SRAM missile.