[PDF] A Study Of Rocket Exhaust Plumes At High Altitudes eBook

Author : Wendell Norman
Publisher :
Page : 179 pages
File Size : 46,11 MB
Release : 1971
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The gas dynamic structure of high altitude rocket plumes has been studied in a low density tunnel to obtain basic data on plume size and shape and to determine the extent of the mixing region between the free-stream and rocket gases. The rocket was simulated by specially designed ejectors using helium and CO2 as the gases, with conditions chosen to simulate a 100,000-lb-thrust rocket at an altitude of 80 km. Data taken included impact pressure surveys, density measurements of the free-stream and plume gas, temperature measurements, and color photographs. The last three of these were taken using electron beam techniques. The result of the study is a set of basic data. Analysis and interpretation of the data will be performed under a separate study. (Author).

Author :
Publisher :
Page : 35 pages
File Size : 27,88 MB
Release : 1969
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A 1-lb-thrust rocket engine was tested to determine plume symmetry and Mach number contours at 400,000-ft altitude. Total pressure surveys were made with and without a flat plate in the plume. The tests without the plate indicated the plume was symmetrical, and measured results compared well with computed values. In tests with the plate, the shock interaction and boundary-layer buildup on the plate were measured.

Author : Larry R. Ring
Publisher :
Page : 107 pages
File Size : 26,62 MB
Release : 1973
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Results are presented of a study for evaluating the applicability and accuracy of rocket motor and exhaust plume gasdynamic analytical models. Evaluation of these analytical models was based upon correlation of analytical predictions with experimental data obtained in the High Altitude Plume Radiation Program. The effects of oxidizer-to-fuel ratio gradients, combustion efficiency, combustion chamber mixing, nozzle throat expansion and chemistry model were ascertained. Non-continuum effects and closed form analytical techniques were also considered. (Modified author abstract).

Author : Frederick P. Boynton
Publisher :
Page : 24 pages
File Size : 25,83 MB
Release : 1972
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Values of impact pressure and species number density measured in a wind tunnel experiment simulating a high-altitude rocket exhaust plume are compared with values calculated with a computer code. Considering a number of uncertainties in the absolute calibrations of the experiment, agreement is generally considered satisfactory for conditions in the mixing region between plume and free stream gases. However, in the forward part of the plume, the data suggests that free-stream gas penetrates further into the plume than the calculation predicts; the cause of this discrepancy is unknown. (Author).

Author : E. Phillip Muntz
Publisher :
Page : 26 pages
File Size : 46,69 MB
Release : 1971
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The study extends the rocket exhaust plume rarefaction scaling of Muntz, Hamel, and Maguire to an external flow. A thrust-altitude map that outlines the various flow regimes was developed. (Author).

Author : Frederick S. Simmons
Publisher : AIAA (American Institute of Aeronautics & Astronautics)
Page : 312 pages
File Size : 43,42 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.

Author : Philip O. Jarvinen
Publisher :
Page : 66 pages
File Size : 19,1 MB
Release : 1966
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The gasdynamic structure of high altitude rocket plumes is investigated. A simple analytical model for the expansion of a gas into a vacuum is constructed and is shown to represent the expansion of exhaust gases from rocket motors into the region bounded by the inner shock wave and Mach disc. A comparison of the exhaust expansion model with solutions obtained with the method of characteristics is made and shows good agreement. Contours of constant density, electron density, and collision frequency in the exhaust plume of a typical rocket engine are determined. The blast wave theory of Hill et al is extended to allow the calculation of the size and shape of rocket plumes of solid propellant missiles. A method is derived which determines the plume drag of solid propellant motors. The method accounts for the fact that solid propellant rocket plume flow is a two phase flow of gas and solids and that the solids present in the exhaust take part in determining the mass flow but not the pressure or the expansion of the exhaust gases upon exit from the rocket nozzle. The plume expansion and resulting plume size is shown to depend on the thrust and the engine exit plane conditions of the gas phase of the two phase flow.