[PDF] Analysis And Correlation Of High Altitude Rocket Exhaust Plume Experimental Data eBook

Author : Larry R. Ring
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Page : 107 pages
File Size : 44,47 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 : Wendell Norman
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Page : 179 pages
File Size : 50,76 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 : Frederick P. Boynton
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Page : 24 pages
File Size : 18,33 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 :
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Page : 538 pages
File Size : 27,49 MB
Release : 1995
Category : Aeronautics
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Author : John T. Neu
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Page : 16 pages
File Size : 37,70 MB
Release : 1960
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The results of computation of the power available from a rocket plume are given. A simplified model was used which assumes the sequential occurrence of exhaust gases expansion to ambient pressure, interaction with the atmosphere, and finally dissipation of power. It is suggested that the experimentally determined drop in radiation at about 180,000 feet is probably due to a power limitation and cessation of afterburning. Power available above about 180,000 feet is due to emission phenomena occurring before the plume equilibrates (expands, etc.) with the ambient atmosphere. It is noted that no fundamental reason exists for expecting missile thrust as a function of altitude to correlate with rocket radiance. A correlation of radiance from different missiles at a given altitude vs thrust has some theoretical justification, however, propellant flow rate is suggested as a better quantity than thrust for this correlation. (Author).

Author :
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Page : 190 pages
File Size : 43,54 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 P. BOYNTON
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Page : 55 pages
File Size : 27,80 MB
Release : 1964
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A method is given for predicting the flow field of a rocket exhaust plume at distances far removed from the nozzle exit at altitudes where afterburning of the exhaust is appreciable. The calculation combines a fluid mechanical analysis of turbulent mixing due to Libby with the adiabatic flame temperature calculation of Boynton and Neu. The eddy viscosity is determined from a consideration of conditions under which compressible turbulent flows appear to exhibit self-preserving behavior. Instructions are given for preparing input to two computer programs which are based on the analysis in the report. In two appendices, it is shown how the eddy viscosity constants may be derived from incompressible jet flow data and a comparison of the results of the present calculation with experimental wind-tunnel rocket exhaust behavior is given. (Author).

Author : Frederick P. Boynton
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Page : 67 pages
File Size : 44,51 MB
Release : 1972
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Further work on the radiative behavior of rocket exhaust plumes at high altitude is reported. Comparisons of calculated flow fields with wind- tunnel test data indicate that agreement is generally satisfactory if allowances are made for absolute calibrations of the data. Calculations of a plume emission according to some proposed mechanisms have been performed. It appears that production of OH by O atom attack on secondary H atoms in hydrocarbon fragments can result in substantial chemiluminescent emission from H2O formed by subsequent reaction of the OH. Some semi-quantitative analogies between rocket exhaust flows and material releases in the upper atmosphere are discussed, and derivations directed toward comparing collision energy distributions at very high altitudes are presented.