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  • 1
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    Report of conference evaluation committee (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A general classification is made of a number of approaches used for the prediction of turbulent shear flows. The sensitivity of these prediction methods to parameter values and initial data are discussed in terms of variable density, pressure fluctuation, gradient diffusion, low Reynolds number, and influence of geometry.
    Keywords: FLUID MECHANICS
    Type: NASA. Langley Res. Center Free Turbulent Shear Flows, Vol. 1; p 673-761
    Format: application/pdf
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  • 2
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    Effects of buoyancy on gas jet diffusion flames - Experiment and theory (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Theoretical and experimental research on the effects of buoyancy on gas-jet diffusion flames is described. Part of this research involves an assessment of existing data obtained under reduced-gravity conditions. The results show that uncertainties in the current understanding of flame structure exist and further research is required before reliable predictions of ignition, stabilization, and propagation of flames under microgravity conditions can be made. Steady-state and transient theories have been developed and used in the analysis of existing drop-tower data and new data obtained from a stationary experiment involving inverted flames. The result of this research has led to the definition of a microgravity experiment to be performed in space.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: IAF PAPER 85-288
    Format: text
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  • 3
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    A mathematical model of a large open fire (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model capable of predicting the detailed characteristics of large, liquid fuel, axisymmetric, pool fires is described. The predicted characteristics include spatial distributions of flame gas velocity, soot concentration and chemical specie concentrations including carbon monoxide, carbon dioxide, water, unreacted oxygen, unreacted fuel and nitrogen. Comparisons of the predictions with experimental values are also given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-166475 , NAS 1.26:166475
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  • 4
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    Multiple-scale turbulence modeling of boundary layer flows for scramjet applications (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of an investigation into the application of turbulence models to the computation of flows in advanced scramjet combustors, the multiple-scale turbulence model was applied to a variety of flowfield predictions. The model appears to have a potential for improved predictions in a variety of areas relevant to combustor problems. This potential exists because of the partition of the turbulence energy spectrum that is the major feature of the model and which allows the turbulence energy dissipation rate to be out of phase with turbulent energy production. The computations were made using a consistent method of generating experimentally unavailable initial conditions. An appreciable overall improvement in the generality of the predictions is observed, as compared to those of the basic two-equation turbulence model. A Mach number-related correction is found to be necessary to satisfactorily predict the spreading rate of the supersonic jet and mixing layer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-3433 , SAI-80-022-CP
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  • 5
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    Buoyancy Effects upon Vapor Flame and Explosion Processes (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of this microgravity project is to develop an experimental and theoretical analyses critical to the understanding of the coupling of buoyancy and turbulence generation and its effect on fuel-air mixing, flame intensity and flame propagation in jet diffusion flames. The experiment is designed to examine certain effects of buoyancy acting on a diffusion flame in which the flame is directed either upward or downward. This change from negative to positive g is observed to significantly alter the flame shape although all other operating conditions are the same for both configurations. However, to perform this experiment a significant coaxial secondary air flow is needed in order to prevent flow reversal when the flame is inverted. The theoretical analysis that has been developed handles the secondary air flow and the extreme change in gravity vector direction. Thus the data will provide a measure of credibility of the analysis which will then be used to assist in the design of the actual zero-g experiment.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Microgravity Sci. and Appl. Program Tasks; p 183
    Format: text
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  • 6
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    Analytic modeling of a spray diffusion flame (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A detailed model for a spray diffusion flame is described. The model is based on the boundary layer form of the equations of motion, with droplet transport accounted for using a discretized droplet size distribution function. Interphase transport of mass and energy are accounted for, with a flame-sheet model used to describe the combustion process on a droplet scale. Near dynamic equilibrium is assumed for the description of droplet transport; droplets can diffuse relative to the gas phase. Gas-phase mixing is accounted for using a two-equation turbulence model; buoyancy effects are included, with a temperature fluctuation equation used to account for buoyancy effects on turbulence structure. Thermal radiation from gas-phase CO2 and H2O is included. Gas-phase chemical kinetics are modeled using a 20-reaction, 10-species version of the advanced quasi-global chemical kinetics formulation. Results are compared with data for a vaporizing Freon spray and a pentane spray flame. It is shown that the computational approach provides a reasonably valid picture of the overall development of a spray diffusion flame, and, furthermore, provides a useful tool for the parametric examination of the spray combustion process.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 84-1317
    Format: text
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  • 7
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    Experimental and theoretical studies of NO/x/ formation in a jet-stirred combustor. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: As an approach to testing kinetic models which couple NO formation to combustion reactions, a jet-stirred combustor was used to study NO(x) formation under kinetically controlled combustion conditions. The experimental data were compared with kinetic calculations for a well-stirred reactor. The agreement between theory and experiment was quite good for the combustion of hydrogen/air and carbon monoxide/air, for which detailed mechanisms were used. A quasi-global mechanism for the combustion of propane/air resulted in substantial underprediction of NO(x) formation.
    Keywords: CHEMISTRY
    Type: International Symposium on Combustion; Aug 20, 1972 - Aug 25, 1972; University Park, PA
    Format: text
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  • 8
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    Analyses for the description of rocket and airbreathing propulsion system combustion chamber and nozzle flows Annual report (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Calculations of rocket and air breathing propulsion system combustion chamber and nozzle flow performance
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-102820 , GASL-TR-736
    Format: application/pdf
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  • 9
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    Some aspects of viscous chemically reacting moderate altitude rocket exhaust plumes Final report (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analytical framework for viscous and chemically reacting plume
    Keywords: FLUID MECHANICS
    Type: NASA-CR-102747 , GASL-TR-737
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  • 10
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    Characterization of the space shuttle reaction control system engine (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program was developed and written in FORTRAN 5 which predicts the transient and steady state performance and heat transfer characteristics of a pulsing GO2/GH2 rocket engine. This program predicts the dynamic flow and ignition characteristics which, when combined in a quasi-steady state manner with the combustion and mixing analysis program, will provide the thrust and specific impulse of the engine as a function of time. The program also predicts the transient and steady state heat transfer characteristics of the engine using various cooling concepts. The computer program, test case, and documentation are presented. The program is applicable to any system capable of utilizing the FORTRAN 4 or FORTRAN 5 language.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-128748 , TMC-S-1220
    Format: application/pdf
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