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  • General Chemistry  (2,783)
  • THERMODYNAMICS AND COMBUSTION  (603)
  • Cell & Developmental Biology
  • 1970-1974  (3,077)
  • 1945-1949
  • 1910-1914  (720)
  • 1973  (1,379)
  • 1971  (1,698)
  • 1912  (720)
Collection
Keywords
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  • 1970-1974  (3,077)
  • 1945-1949
  • 1910-1914  (720)
Year
  • 1
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    A new look at AP/composite propellant combustion (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Some theoretical studies on the time-independent and oscillatory combustion of nonmetallized ammonium perchlorate (AP)/composite propellants are presented. A coherent and unified interpretation was made of the voluminous data available from experiments related to propellant combustion. Three fundamental hypotheses are introduced: the extent of propellant degradation at the vaporization step has to be specified through a scientific criterion; the condensed-phase degradation reaction of ammonium perchlorate to a vaporizable state is the overall rate-limiting step; gas-phase combustion rate is controlled by the mixing rate of fuel and oxidizer vapors. In the treatment of oscillatory combustion, the assumption of quasi-steady fluctuations in the gas phase is used to supplement these hypotheses.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-77
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  • 2
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    Inflight thermodynamic properties (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-02
    Description: The inflight thermodynamic parameters (temperature, pressure, and density) of the atmosphere are presented. Mean and extreme values of the thermodynamic parameters given here can be used in application of many aerospace problems, such as: (1) research and planning and engineering design of remote earth sensing systems; (2) vehicle design and development; and (3) vehicle trajectory analysis, dealing with vehicle thrust, dynamic pressure, aerodynamic drag, aerodynamic heating, vibration, structural and guidance limitations, and reentry analysis. Atmospheric density plays a very important role in most of the above problems. A subsection on reentry is presented, giving atmospheric models to be used for reentry heating, trajectory, etc., analysis.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Terrest. Environ. (Climatic) Criteria Guidelines for Use in Aerospace Vehicle Develop., 1973 Rev.; 34 p
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  • 3
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    Solar heating and cooling buildings (1973)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Sunshine is available in differing amounts everywhere in the world and the easiest method of capturing it is by absorption in the form of thermal energy (heat). Therefore, it is logical to utilize it directly in the heating and cooling of buildings and avoid losses that would occur by conversion to some other form. It may be emphasized that of the total energy consumed annually in the U.S., about 25% is used for heating and cooling in buildings. It is generally agreed that of all the possible widespread uses of solar energy, this application has the highest probability of success in the near term. Although there are significant uncertainties associated with some technological and economic aspects, they do not loom as large as those associated with other potentially significant applications, such as electrical power generation. It may, however, be noted that solar electrical power generation at the building site, or at a centralized station is an excellent long term prospect. Approximately 25 experimental solar heated structures have been built in various parts of the world.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 28 p
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  • 4
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    Shape of porous cooled region for surface heat flux and temperature both specified. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 16; Sept
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  • 5
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    Assessment of chemical nonequilibrium for massively ablating graphite. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Several types of artificial graphite have been irradiated by laser pulses in vacuum, and the composition of the resulting vapor cloud has been determined in situ by mass spectrometric techniques in order to gain information pertaining to nonequilibrium ablation of graphitic probes entering planetary atmospheres. Results are discussed in terms of variations in concentrations of carbon species from their equilibrium values, and plotted curves illustrate the effect of nonequilibrium ablation on radiative shielding for simulated Jupiter entry conditions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Aug. 197
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  • 6
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    Transient forced convection heat transfer from an isothermal flat plate. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An analysis is presented for laminar transient forced-convection heat transfer from a horizontal flat plate. The presented analysis results include transient velocity and temperature profiles, boundary-layer growth rate, and heat-transfer rate with time.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; June 197
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  • 7
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    Measurements of hydrogen-helium radiation at shock-layer temperatures appropriate for Jupiter entry. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Shock waves traveling at approximately 16 km/sec into a gas mixture of 7% H2 and 93% He were used to simulate the shock-layer conditions for a representative shallow entry into the Jovian atmosphere. The absolute intensities of line and continuum radiation were measured and the radiative cooling of the shock-heated gas is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 13; Oct. 197
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  • 8
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    Strategy for solar heating and cooling in buildings (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The types of solar energy heating and cooling equipment for use with buildings are discussed. The steps from manufacturing to equipment installation are identified. A feasibility study for the use of solar energy was conducted. The study determined the technical, environmental, economic, sociological, political, and strategic aspects of solar heating and cooling.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 159 p
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  • 9
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    Market potential for solar heating and cooling in buildings (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The use of solar heating and cooling for buildings as a method of conserving fossil fuels is discussed. The residential and commercial end use consumption of energy is tabulated. A survey to project the energy requirements for home and industry heating and cooling is developed. The survey indicates that there is a market potential for solar heating and cooling of buildings. A prediction of three to five billion dollars per year as the potential for solar heating and cooling is made.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: TERRASTAR: Terrest. Appl. of Solar Technol. and Res.; 13 p
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  • 10
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    Thermal shielding by subliming volume reflectors in convective and intense radiative environments. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The behavior of dielectric materials having densely packed internal scattering centers subject to extreme convective and radiative environments is analyzed. Experiments have shown that these materials act as volume reflectors of incident radiation even when the exposed surface is being eroded by thermochemical ablation. The analysis was applied to interpret experiments of subliming Teflon models exposed to combined radiative and convective fluxes up to 1.7 kW/sq cm for several seconds. Results show that, although the exposed surface receded at an apparently steady rate, the internal temperature climbed continually, due to internal absorption of radiation and would have caused failure internally if the test duration were extended a few seconds. Thus, performance is time-limited by the internal absorption coefficient. Results were obtained for larger configurations and other materials. Typically, Teflon shells may withstand radiant fluxes up to 20 kW/sq cm for about 5 sec and fritted quartz up to 50 kW/sq cm for about 8 sec (corresponding to the Jupiter entry).
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; July 197
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  • 11
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    Effect of surface catalytic activity on stagnation heat-transfer rates. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: An experiment was made to determine the effect heterogeneous catalytic surface reactions have on heat-transfer rates in highly frozen low-density stagnation-point boundary layers. Data were obtained in arc-heated facilities that were capable of producing large percentages of chemical energy frozen in a supersonic freestream. The heat-transfer rate to a silicon-dioxide surface was reduced to a minimum value of only one-third of the value obtained on relatively active nickel and platinum surfaces. This is the result of its low catalytic efficiency. Ionization energy was recovered on both the active and the inactive surfaces, indicating that this energy either was released many times faster than the recombination energy or was not controlled by the surface composition.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
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  • 12
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    Interaction of free and forced convection in horizontal tubes in the transition regime. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experimental investigation of some new aspects of the combined free and forced convection interacting in the transition regime of a horizontal tube under uniform heat flux conditions. The results obtained include indications that thermally induced secondary flows attenuate the fluctuations in low inlet turbulence flows, while they restabilize the flow as the inlet turbulence is increased.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Fluid Mechanics; 57; Feb. 6
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  • 13
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    Stagnation region radiative heating with steady-state ablation during Venus entry. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 10; Feb. 197
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  • 14
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    The energy situation (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Energy reserves from the principal energy sources other than petroleum and natural gas are summarized. It was found that energy sources are being consumed at rates which exceed the ability to replace them through new discoveries and technology improvements. The costs and implications to environment for using coal and nuclear energy are discussed. Tables are presented on energy consumption, cost of reclamation, and water power capacity.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: The Energy Dilemma and Its Impact on Air Transportation; p 1-48
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  • 15
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    An improved separability approximation for line radiative transport in nonhomogeneous media. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: A simple modification to the constant half-width approximation of Wilson and Greif, which is an extension of the well-known Curtis-Godson method to the treatment of temperature variations along the integration path, is introduced which permits a more accurate evaluation of line radiative transport in nonhomogeneous gases. To demonstrate the method's accuracy, comparisons are made with Wilson and Greif and numerical frequency integrated results for the line equivalent width and radiative flux in a planar slab with prescribed Planck function and line half-width spatial variations. These variations are chosen to represent typical shock layer conditions. It is found that the modified procedure reduces the inaccuracies inherent in Wilson and Greif's approximation by factors ranging from 5 to 10, while retaining the latter method's ease of application.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Quantitative Spectroscopy and Radiative Transfer; 13; June 197
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  • 16
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    Nonlinear least squares - An aid to thermal property determination. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Nonlinear least squares techniques can be used to determine effective thermal conductivity values from experimental data. Comparisons between measured and predicted conductivity values indicate that the analytically determined values can be used with confidence in performing thermal protection system analyses. A study was performed to compare the relative efficiencies of different minimizing techniques; the method of Peckham was the most efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; May 1973
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  • 17
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    Analysis of sublimation-cooled coated mirrors in convective and radiative environments. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Analytical solutions were obtained for the thermal response of a transpiration- or sublimation-cooled spherical mirror coating exposed to convective and radiative heating. The solutions allow unlimited spectral detail to be accounted for. Results indicate that transpiration-cooled thick coatings (1 cm) may withstand up to 10 kW/sq cm on a steady basis without excessive temperature rise for quartzlike materials with an internal absorption coefficient of 0.01 per cm. On a transient basis, fluxes up to 20 kW/sq cm can be accommodated for a second (cW laser exposure time), 4 kW/sq cm for 5 sec (planetary entry heating time), and of the order of MW/sq cm for millisecond times (short-duration laser bursts) without transpiration cooling for a material with an absorption coefficient of 0.1 per cm. Proportionately higher fluxes can be accommodated with lower absorption coefficients. Thermal stresses produced by the heat pulse are found to be high but within the strength of the materials. The regime in which meaningful solutions may be obtained is mapped in detail.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Jan. 197
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  • 18
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    Variational solution to the radiative equation by the use of a step function. II - Extension to nonlinear case by iteration method. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Jan. 197
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  • 19
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    Radiation configuration factors for annular rings and hemispherical sectors. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: In the application of Monte Carlo computer techniques to the study of problems in the free molecular flow regime, the analogy between radiation heat transfer with diffuse emissions and the free molecular flow field makes it possible to use the radiation configuration factors as a test on the operation of the Monte Carlo program. A source plane which was an annular ring of arbitrary radius around a sphere with the center of the disk coincident with the center of the sphere was examined. Since various indicators seemed to verify the correct operation of the program, the program was used to calculate the radiation configuration factors. The study adds a new geometry to the general literature on radiation configuration factors.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 20
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    Laminar film boiling on inclined isothermal flat plates. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Laminar film boiling from an inclined flat plate has been investigated analytically. Using the singular perturbation scheme, the complete set of Navier-Stokes equations is solved. The zeroth-order perturbation coinciding with the boundary-layer equations for vertical flat plates governs the problem. The higher-order perturbations become important near the leading edge and for large values of the inclination angle from the vertical. The assumption of zero interfacial velocity shows that, except for fluids having large (rho x mu) ratios, the results can be predicted using the vertical flat plate results by defining a modified Grashof parameter containing a cos phi term. When the interfacial shear is considered, the solutions indicate that for fluids having large (rho x mu) ratios, the heat transfer rates will be larger (approximately 15% maximum) than those predicted by the simplified model using zero interfacial velocity. In general, the inclination decreases the rate of heat transfer as well as the rate of evaporation.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Jan. 197
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  • 21
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    Heat pipe flight experiments (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: OAO 3 heat pipe flight experiments to check out weightlessness behavior are reported. Tested were a hollow channel screen system with helical grooves, a heat pipe with a wicking system of horizontal grooves, and a spiral artery pipe with multichannel fluid return to the evaporator. Flight experiment data proved that all heat pipe geometries containing wicking systems provided uninterrupted fluid return to the condensators during weightlessness and sufficient cooling for isothermalizing optical instruments onboard OAO.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Significant Accomplishments in Technol., 1972; p 37-41
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  • 22
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    Environmental compatibility of the all-silica rigid surface insulation (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Testing has demonstrated the compatibility of the all-silica surface insulation system to a variety of space shuttle orbiter environmental aspects for launch, on-orbit, and special reentry conditions. Among the more important results are the success of the cold soak tests, which indicate the suitability of the foam/bond attachment system with a 2 mm thick foam pad for strain isolation, and the reentry temperature overshoot tests (to 1924 K), which show that this system can tolerate considerable dispersion in reentry heating environment.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 709-730
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  • 23
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    Environmental testing of REI-Mullite thermal protection system for the space shuttle orbiter (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Tests conducted to evaluate performances in the natural environments of salt spray, humidity, rain, vacuum, and cryogenic temperatures have shown the ceramic mullite fiber is completely compatible and that these environments have no adverse effects on subsequent mission performance. Rain erosion testing has indicated a damage threshold that must be accounted for in the final design. Tests conducted to evaluate the performance of ceramic mullite fiber to induced acoustic, re-entry, and structural load environments again have shown complete capability to fulfill mission environments. Although minor cracking of the sidewall coating was seen to occur throughout the induced environment test program, sidewall designs configured to provide increased flexibility have been successfully tested.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 2; p 667-708
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  • 24
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    Results of RSI Thermal-structural Analysis (1973)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: Thermostructural comparisons of mullite and silica reusable surface insulation materials for space shuttle application show that mullite is much more subject to thermal stress failure than silica composite materials.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 3; p 1227-1267
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  • 25
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    A Non Rigid Reusable Surface Insulation Concept for the Space Shuttle Thermal Protection System (1973)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: A reusable thermal protection system concept was developed for the space shuttle that utilizes a flexible, woven ceramic mat insulation beneath an aerodynamic skin and moisture barrier consisting of either a dense ceramic coating or a super alloy metallic foil. The resulting heat shield material has unique structural characteristics. The shear modulus of the woven mat is very low such that bending and membrane loads introduced into the underlying structural panel remain isolated from the surface skin.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Ames Res. Center Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 3; p 1185-1225
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  • 26
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    Interference Heating to Cavities Between Simulated RSI Tiles (1973)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: Test results for full scale simulated surface insulation tiles on both the tunnel wall and in the free stream, for in-line and staggered tile orientations, are summarized as follows: (1) The staggered tile orientation has heating on the forward face which is a factor of 4.5 times higher than the heating to the forward face of the in-line tile orientation; (2) the longitudinal gap heating was the highest for the 0.3175 cm gap and the lowest for the 0.1587 cm gap; and (3) there was an order of magnitude decrease in the heating on the forward face of a spanwise gap when the gap size was decreased from 0.3175 cm to 0.1587 cm.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Symp. on Reusable Surface Insulation for Space Shuttle, Vol. 3; p 1269-1276
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  • 27
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    Development of low-shock pyrotechnic separation nuts (1973)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Performance demonstrations and comparisons were made on six flight type pyrotechnic separation nut designs, two of which are standard designs in current use, and four of which were designed to produce low shock on actuation. Although the shock performances of the four low shock designs are considerably lower than the standard designs, some penalties may be incurred in increased volume, weight, or complexity. These nuts, and how they are installed, can significantly influence the pyrotechnic shock created in spacecraft structures. A high response monitoring system has been developed and demonstrated to provide accurate performance comparisons for pyrotechnic separation nuts.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: The 8th Aerospace Mech. Symp. te; p 179-212
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  • 28
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    WASP: A flexible FORTRAN 4 computer code for calculating water and steam properties (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A FORTRAN 4 subprogram, WASP, was developed to calculate the thermodynamic and transport properties of water and steam. The temperature range is from the triple point to 1750 K, and the pressure range is from 0.1 to 100 MN/m2 (1 to 1000 bars) for the thermodynamic properties and to 50 MN/m2 (500 bars) for thermal conductivity and to 80 MN/m2 (800 bars) for viscosity. WASP accepts any two of pressure, temperature, and density as input conditions. In addition, pressure and either entropy or enthalpy are also allowable input variables. This flexibility is especially useful in cycle analysis. The properties available in any combination as output include temperature, density, pressure, entropy, enthalpy, specific heats, sonic velocity, viscosity, thermal conductivity, surface tension, and the Laplace constant. The subroutine structure is modular so that the user can choose only those subroutines necessary to his calculations. Metastable calculations can also be made by using WASP.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7391 , E-7339
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  • 29
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    The effect of water injection on nitric oxide emissions of a gas turbine combustor burning ASTM Jet-A fuel (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted to determine the effect of water injection on oxides of nitrogen (NOx) emissions of a full annular, ram induction gas turbine combustor burning ASTM Jet-A fuel. The combustor was operated at conditions simulating sea-level takeoff and cruise conditions. Water at ambient temperature was injected into the combustor primary zone at water-fuel ratios up to 2. At an inlet-air temperature of 589 K (600 F) water injection decreased the NOx emission index at a constant exponential rate: NOx = NOx (o) e to the -15 W/F power (where W/F is the water-fuel ratio and NOx(o) indicates the value with no injection). The effect of increasing combustor inlet-air temperature was to decrease the effect of the water injection. Other operating variables such as pressure and reference Mach number did not appear to significantly affect the percent reduction in NOx. Smoke emissions were found to decrease with increasing water injection.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2958 , E-7531
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  • 30
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    HNS/Teflon, a new heat resistant explosive (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: HNS/Teflon (90/10) is a new pressed explosive developed for use in the Apollo program. The major advantages of HNS/Teflon are (1) excellent thermal stability at elevated temperatures, (2) superior resistance to sublimation at high temperatures and low pressures and (3) ease of molding powder preparation, pressing and machining. The impact sensitivity of HNS/Teflon is between that of Comp B and Comp A-3 while its explosive performance is about the same as TNT. Under the severe environmental conditions of the moon's surface, this explosive successfully performed its intended function of generating seismic waves in the Apollo ALSEP and LSPE experiments. (Modified author abstract)
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-136530 , AD-767932 , NOLTR-73-163
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  • 31
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    Effect of increased fuel temperature on emissions of oxides of nitrogen from a gas turbine combustor burning natural gas (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An annular gas turbine combustor was tested with heated natural gas fuel to determine the effect of increasing fuel temperature on the formation of oxides of nitrogen. Fuel temperatures ranged from ambient to 800 K (980 F). Combustor pressure was 6 atmospheres and the inlet air temperature ranged from 589 to 894 K (600 to 1150 F). The NOx emission index increased with fuel temperature at a rate of 4 to 9 percent per 100 K (180 F), depending on the inlet air temperature. The rate of increase in NOx was lowest at the highest inlet air temperature tested.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2930 , E-7618
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  • 32
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    User's manual for the TRW gaspipe 2 program: A vapor-gas front analysis program for heat pipes containing non-condensible gas (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital computer program for design and analysis of heat pipes which contain non-condensible gases, either for temperature control or to aid in start-up from the frozen state, is presented. Some of the calculations which are possible with the program are: (1) wall temperature profile along a gas-loaded heat pipe, (2) amount of gas loading necessary to obtain desired evaporator temperature at a desired heat load, (3) heat load versus evaporator temperature for a fixed amount of gas in the pipe, and (4) heat and mass transfer along the pipe, including the vapor-gas front region.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114672 , TRW-13111-6054-RO-00
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    Investigation of low-cost fabrication of ablative heat shields (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The fabrication, testing, and evaluation of materials and techniques employed in the fabrication of ablative heat shield panels are described. Results of this effort show projected reductions in labor man-hours for dielectric curing of panels when compared to panels molded in a steam-heated press. In addition, panels were fabricated with more than one density within the cross-section. These dual-density panels show significant weight and cost reduction potentials.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-112312 , BC-8838-FR
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    Integrated circuit package with lead structure and method of preparing the same (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A beam-lead integrated circuit package assembly including a beam-lead integrated circuit chip, a lead frame array bonded to projecting fingers of the chip, a rubber potting compound disposed around the chip, and an encapsulating molded plastic is described. The lead frame array is prepared by photographically printing a lead pattern on a base metal sheet, selectively etching to remove metal between leads, and plating with gold. Joining of the chip to the lead frame array is carried out by thermocompression bonding of mating goldplated surfaces. A small amount of silicone rubber is then applied to cover the chip and bonded joints, and the package is encapsulated with epoxy resin, applied by molding.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    High powered arc electrodes (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Nonconsumable metal electric arc electrodes are described capable of being operated in a variety of gases at various pressures, current, and powers. The cathode has a circular annulus tip to spread the emission area for improved cooling.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 36
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    Digital second-order phase-locked loop (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digital second-order phase-locked loop is disclosed in which a counter driven by a stable clock pulse source is used to generate a reference waveform of the same frequency as an incoming waveform, and to sample the incoming waveform at zero-crossover points. The samples are converted to digital form and accumulated over M cycles, reversing the sign of every second sample. After every M cycles, the accumulated value of samples is hard limited to a value SGN = + or - 1 and multiplied by a value delta sub 1 equal to a number of n sub 1 of fractions of a cycle. An error signal is used to advance or retard the counter according to the sign of the sum by an amount equal to the sum.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    Analysis of transient heat flow to thick-walled plates and cylinders (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A methodology is described for the analysis of a transient temperature measurement made in a flat or curved plate subjected to convective heat transfer, such that the surface heat flux, the hot-gas temperture, and the gas heat transfer coefficient can be determined. It is shown that if the transient temperature measurement is made at a particular point located nearly midway in the thickness of the plate there is an important simplification in the data analysis process, in that the factor relating the surface heat flux to the measured rate of rise of temperature becomes invariant for a Fourier Number above 0.60 and for all values of the Biot Number. Parameters are derived, tabulated, and plotted which enable straightforward determination of the surface heat flux, the hot-gas temperature, of the plate, the rate of rise of temperature, the plate thickness and curvature, and the mean thermal properties of the plate material at the test temperature.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-136226 , JPL-TR-32-1588
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  • 38
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    Spontaneous ignition in afterburner segment tests at an inlet temperature of 1240 K and a pressure of 1 atmosphere with ASTM jet-A fuel (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A brief testing program was undertaken to determine if spontaneous ignition and stable combustion could be obtained in a jet engine afterburning operating with an inlet temperature of 1240 K and a pressure of 1 atmosphere with ASTM Jet-A fuel. Spontaneous ignition with 100-percent combustion efficiency and stable burning was obtained using water-cooled fuel spraybars as flameholders.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2952 , E-7560
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    Thermal engineering research (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A theoretical investigation of gas flow inside a multilayer insulation system has been made for the case of the broadside pumping process. A set of simultaneous first-order differential equations for the temperature and pressure of the gas mixture was obtained by considering the diffusion mechanism of the gas molecules through the perforations on the insulation layers. A modified Runge-Kutta method was used for numerical experiment. The numerical stability problem was investigated. It has been shown that when the relaxation time is small compared with the time period over which the gas properties change appreciably, the set of differential equations can be replaced by a set of algebraic equations for solution. Numerical examples were given, and comparisons with experimental data were made.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-124481 , UAH-146
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  • 40
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    Thermodynamic and transport properties of air and its products of combustion with ASTMA-A-1 fuel and natural gas at 20, 30, and 40 atmospheres (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The isentropic exponent, molecular weight, viscosity, specific heat at constant pressure, thermal conductivity, Prandtl number, and enthalpy were calculated for air, the combustion products of ASTM-A-1 jet fuel and air, and the combustion products of natural gas and air. The properties were calculated over a temperature range from 300 to 2800 K in 100 K increments and for pressures of 20, 30 and 40 atmospheres. The data for natural gas and ASTM-A-1 were calculated for fuel-air ratios from zero to stoichiometric in 0.01 increments.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7488 , E-7523
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  • 41
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    Use of an air-assisted fuel nozzle to reduce idle emissions of a jt8d engine combustor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were performed at typical engine idle conditions on a single-can JT8D combustor installed in a 24 centimeter (9.45 in.) housing to evaluate the effect of an air-assist nozzle on reducing exhaust emissions. By injecting high-pressure air through the secondary-flow passage of a standard duplex fuel nozzle, it was possible to reduce hydrocarbon emissions from 840 parts per million to 95 parts per million and carbon monoxide emissions from 873 parts per million to 258 parts per million. NOX emissions increased slightly from 18 parts per million to 22 parts per million. An air-assist differential pressure of only 20.1 newtons per square centimeter (29.1 psi) and an airflow rate of only 0.22 percent of the total combustor airflow was required.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2946 , E-7580
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    Effect of gage size on the measurement of local heat flux (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: General formulas are derived for determining gage averaging errors of strip-type heat flux meters used in the measurement of one-dimensional heat flux distributions. In addition, a correction procedure is presented which allows a better estimate for the true value of the local heat flux. As an example of the technique, the formulas are applied to the cases of heat transfer to air slot jets impinging on flat and concave surfaces. It is shown that for many practical problems, the use of very small heat flux gages is often unnecessary.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2943 , E-7526
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  • 43
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    Figure-of-merit calculation methods for organic heat-pipe fluids (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: With only chemical formulas and operating temperatures specified, selected correlating equations and tables of chemistry-effect functions allow estimates of figures of merit for organic heat-pipe-fluids.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2945 , E-7632
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    A hydrogen energy carrier. Volume 2: Systems analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A systems analysis of hydrogen as an energy carrier in the United States indicated that it is feasible to use hydrogen in all energy use areas, except some types of transportation. These use areas are industrial, residential and commercial, and electric power generation. Saturation concept and conservation concept forecasts of future total energy demands were made. Projected costs of producing hydrogen from coal or from nuclear heat combined with thermochemical decomposition of water are in the range $1.00 to $1.50 per million Btu of hydrogen produced. Other methods are estimated to be more costly. The use of hydrogen as a fuel will require the development of large-scale transmission and storage systems. A pipeline system similar to the existing natural gas pipeline system appears practical, if design factors are included to avoid hydrogen environment embrittlement of pipeline metals. Conclusions from the examination of the safety, legal, environmental, economic, political and societal aspects of hydrogen fuel are that a hydrogen energy carrier system would be compatible with American values and the existing energy system.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134176
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  • 45
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    A hydrogen energy carrier. Volume 1: Summary (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The production, technology, transportation, and implementation of hydrogen into the energy system are discussed along with the fossil fuel cycle, hydrogen fuel cycle, and the demands for energy. The cost of hydrogen production by coal gasification; electrolysis by nuclear energy, and solar energy are presented. The legal aspects of a hydrogen economy are also discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-134175
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  • 46
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    A laser initiated explosive device system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A laser initiated explosive system has been developed which can simultaneously initiate multiple explosive devices. Advantages of this system over electrically initiated devices (EED's) are increased safety and reliability, simplicity of laser initiated devices, and increased weight efficiency. The system design with test data are presented and a comparison between laser initiation and electrical initiation is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Langley Res. Center The 8th Aerospace Mech. Symp.; p 25-35
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  • 47
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    Fluid pressure amplifier and system (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flueric beam-deflection amplifier and a method of controlling the same are described. Either a single or a series of cascaded fluid amplifier units are provided and each one of which may include the usual power nozzle, control nozzles, outlet passages and vent passages. All vent passages of each fluid amplifier unit lead to an enclosed vent outlet chamber which is connected to the ambient environment or to a return manifold through a variably restricted passage. To control the fluid amplifier unit, power and control stream pressures are first established, after which the restricted passage is reduced to regulate the input bias, the gain and the input impedance of the fluid amplifier unit.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    The control of carbon dioxide cryodeposits (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental study has been conducted to investigate the parameters affecting the cryodeposition of carbon dioxide frost. In the investigation carbon dioxide frost was cryodeposited from a helium-carbon dioxide mixture into a layer of fibrous insulation surrounding a cylindrical cryogenic tank. Results of the study indicated that not only did deposition occur on the frost surface but also within the frost layer. Over the range of variables investigated both the frost density and the mass of frost deposited were most sensitive to the time of deposition, the percent of carbon dioxide in the purge-gas mixture, and the thickness of the insulation. Frost density and mass of frost deposition were found to increase with time and percent carbon dioxide, and to decrease with increasing insulation thickness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7334 , L-8884
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    Electron beam controller (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: An electron beam device which extracts energy from an electron beam before the electrons of the beam are captured by a collector apparatus is described. The device produces refocusing of a spent electron beam by minimizing tranverse electron velocities in the beam where the electrons, having a multiplicity of axial velocities, are sorted at high efficiency by collector electrodes.
    Keywords: THERMODYNAMICS AND COMBUSTION
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    Theory for radiatively driven harmonic acoustic waves in a confined gas. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A detailed theoretical study is made of radiatively driven acoustic waves inside a closed cylindrical tube. The formulation accounts for all the essential phenomena for a gas in vibrational equilibrium - namely, gas motion, longitudinal and radial viscous dissipation, longitudinal and radial heat conduction, and radiative transfer with spectral detail included. An approximate expression is derived for the pressure response. This solution is applicable to arbitrary spectral distribution of the radiative absorption coefficient, under conditions attainable in the laboratory. The solution includes both tuned and untuned acoustic conditions as well as the spectrophone limit - that is, the condition where the length of the tube is much smaller than the length of the acoustic wave. The influence of spectral detail on the pressure response is illustrated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-776848 , AFOSR-74-0403TR , Physics of Fluids; 16; Aug. 197
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  • 51
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    Simultaneous control of temperature and humidity in a confined space. I - Mathematical modeling of the dynamic behavior of temperature and humidity in a confined space. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Building Science; 8; 1973
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    Laminar film condensation on the inside of slender, rotating truncated cones. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: A solution for film condensation on the inside of slender rotating truncated cones is established in the region where the half cone angle phi is close to zero and where the equation of Dhir and Lienhard (1971) is no longer valid. All the familiar assumptions used in Nusselt's theory of laminar film condensation are assumed valid, including negligible sub-cooling and momentum changes in the condensate film, no interfacial shear between the condensate and the vapor, and pure conduction within the condensate film. A Runge-Kutta numerical integration method using a digital computer was used. Results for a specific geometry are given for water condensing at 212 F on a condenser wall maintained at 70 F.
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    Experimental verification of the energy dissipation mechanism in acoustic dampers. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: An experimental program is described which verifies the theoretical model that acoustic damping devices undergoing high intensity oscillations dissipate energy via jet kinetic losses. Pressure measurements within the damping devices and flow duct together with detailed surveys of the jet velocities provide the experimental confirmation. The theory accounts for duct flow effects, both steady and unsteady, as well as the jet dissipation. Discrepancies between theory and experiment can be traced to neglect of higher order terms or ignoring the difficult wall friction term in the case of the quarter-wave tube.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Sound and Vibration; 26; Jan. 22
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  • 54
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    Variable conductance heat pipes from the laboratory to space (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat pipes were developed which can be used as (1) a variable conductance link between a heat source and sink which provides temperature stability; (2) a feedback control mechanism that acts to directly maintain the source at a constant temperature; (3) or as a thermal diode that allows heat to be transferred in one direction only. To establish flight level confidence in these basic control techniques, the Ames Heat Pipe Experiment (AHPE) was launched in August 1972 and the Advanced Thermal Control Flight Experiment (ATFE) is scheduled for launch in May 1973. The major efforts of the technology development, initial flight results of the AHPE, and ground test data of the ATFE are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-62290
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  • 55
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    Net radiation method for enclosure systems involving partially transparent walls (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The net radiation method is developed for analyzing radiation heat transfer in enclosure systems involving partially transparent walls. One such system is an enclosure with windows in it. The conventional net radiation method was developed for enclosures having opaque walls. If a partially transparent wall is present, it will permit radiation to enter and leave the enclosure. The net radiation equations are developed here for gray and semigray enclosures with one or more windows. Another system of interest, such as in a flat plate solar collector, consists of a series of parallel transparent layers. The transmission characteristics of such window systems are obtained by the net radiation method, and the technique appears to be more convenient than the ray tracing method which has been used in the past. Relations are developed for windows consisting of any number of parallel layers having differing absorption coefficients and differing surface reflectivities, and for systems composed of parallel transmitting layers and opaque plates.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7384 , E-7363
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  • 56
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    Afterburner performance of film-vaporizing V-gutters for inlet temperatures up to 1255 K (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Combustion tests of five variations of an integral, spray-bar - flameholder combination were conducted in a 0.49-m-diameter duct. Emphasis was on low levels of augmentation. Fuel impinged on guide plates, mixed with a controlled amount of inlet air, vaporized, and was guided into the V-gutter wake. Combustor length was 0.92 m. Good performance was demonstrated at fuel-air ratios less than 0.025 for inlet temperatures of 920 to 1255 K. Maximum combustion efficiency occured in the vicinity of fuel-air ratios of 0.02 and was 92 to 100 percent, depending on the inlet temperature. Lean blowout fuel-air ratios were in the vicinity of 0.005. Improvements in rich-limit blowout resulted from enlarging the guide-flow passageway areas. Other means of extending the operating range are suggested. A simplified afterburner concept for application to advanced engines is described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2855 , E-7435
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    Performance of an annual combustor designed for a low-cost turbojet engine (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance tests were conducted on a combustor designed for use in a low-cost turbojet engine. Low-cost features included the use of very inexpensive simplex fuel nozzles and combustor liners of perforated sheet material. Combustion efficiencies at the altitude-cruise and sea-level design points were approximately 94 and 96 percent, respectively. The combustor isothermal total-pressure loss was 8.8 percent at the altitude-cruise-condition diffuser-inlet Mach number of 0.335. The combustor-exit temperature pattern factor was less than 0.3 at the altitude-cruise, sea-level-cruise, and sea-level-static design conditions. The combustor-exit average radial temperature profiles at all conditions were in very good agreement with the design profile. The intense mixing required because of the very high combustor heat-release rate had an adverse effect on ignition capability at altitude windmilling design conditions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2857 , E-7424
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    Extended hydrodynamic theory of the peak and minimum pool boiling heat fluxes (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The hydrodynamic theory of the extreme pool boiling heat fluxes is expanded to embrace a variety of problems that have not previously been analyzed. These problems include the prediction of the peak heat flux on a variety of finite heaters, the influence of viscosity on the Taylor and Helmoltz instability mechanisms with application to film boiling and to the peak heat flux in viscous liquids, the formalization of the analogy between high-current-density electrolysis and boiling, and the description of boiling in the low-gravity limit. The predictions are verified with a large number of new data.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-2270
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  • 59
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    Handbook of infrared radiation from combustion gases (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: The treatment of radiant emission and absorption by combustion gases are discussed. Typical applications include: (1) rocket combustion chambers and exhausts, (2) turbojet engines and exhausts, and (3) industrial furnaces. Some mention is made of radiant heat transfer problems in planetary atmospheres, in stellar atmospheres, and in reentry plasmas. Particular consideration is given to the temperature range from 500K to 3000K and the pressure range from 0.001 atmosphere to 30 atmospheres. Strong emphasis is given to the combustion products of hydrocarbon fuels with oxygen, specifically to carbon dioxide, water vapor, and carbon monoxide. In addition, species such as HF, HC1, CN, OH, and NO are treated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-3080
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  • 60
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    Thermodynamic and transport properties of gaseous tetrafluoromethane in chemical equilibrium (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Equations and in computer code are presented for the thermodynamic and transport properties of gaseous, undissociated tetrafluoromethane (CF4) in chemical equilibrium. The computer code calculates the thermodynamic and transport properties of CF4 when given any two of five thermodynamic variables (entropy, temperature, volume, pressure, and enthalpy). Equilibrium thermodynamic and transport property data are tabulated and pressure-enthalpy diagrams are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7181 , L-8483
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    Heat transfer characteristics of a single circular air jet impinging on a concave hemispherical shell (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental study was made of the local and average heat-transfer characteristics of a single turbulent air jet impinging on the concave surface of a hemisphere. Correlations were developed for expressing the effects of a number of dimensionless variables on the local and average Nusselt numbers. Results of the present study are compared with those from a similar study concerning a concave surface of a semicylindrical shell.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2859 , E-7462
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    Thermal conductivity of particulate materials: A summary of measurements taken at the Marshall Space Flight Center (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Thermal conductivity measurements of particulate materials in vacuum are presented in summary. Particulate basalt and soda lime glass beads of various size ranges were used as samples. The differentiated line heat source method was used for the measurements. A comprehensive table is shown giving all pertinent experimental conditions. Least-squares curve fits to the data are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-64759
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  • 63
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    Startup analysis for a high temperature gas loaded heat pipe (1973)
    In:  CASI
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    Publication Date: 2019-06-27
    Description: A model for the rapid startup of a high-temperature gas-loaded heat pipe is presented. A two-dimensional diffusion analysis is used to determine the rate of energy transport by the vapor between the hot and cold zones of the pipe. The vapor transport rate is then incorporated in a simple thermal model of the startup of a radiation-cooled heat pipe. Numerical results for an argon-lithium system show that radial diffusion to the cold wall can produce large vapor flow rates during a rapid startup. The results also show that startup is not initiated until the vapor pressure p sub v in the hot zone reaches a precise value proportional to the initial gas pressure p sub i. Through proper choice of p sub i, startup can be delayed until p sub v is large enough to support a heat-transfer rate sufficient to overcome a thermal load on the heat pipe.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2840 , E-7416
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  • 64
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    Comparison of temperature data from an engine investigation for film-cooled and non-film-cooled, panwise-finned vanes incorporating impingement cooling (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The experimental temperature characteristics of two spanwise-finned, impingement-cooled vanes, one with film cooling and one without film cooling, were investigated in a modified J-75 research turbojet engine. Values of maximum temperature, average temperature, and maximum chordwise temperature difference were compared for the two vanes at the midspan. An analytical redesign of the two vane configurations indicated that the maximum and average temperatures and the maximum chordwise temperature difference could be significantly lowered. The experimental tests indicated that suction-surface film cooling may cause increased heat transfer near the trailing edge of the vane.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2819 , E-7386
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    Heat flow and convection demonstration (Apollo 14) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Apollo 14 Astronaut Stuart A. Roosa conducted a group of experiments during the lunar flyback on February 7, 1971, to obtain information on heat flow and convection in gases and liquids in an environment of less than 0.000001 g. Flow observations and thermal data have shown that: (1) as expected, there are convective motions caused by surface tension gradients in a plane liquid layer with a free upper surface; (2) heat flow in enclosed liquids and gases occurs mainly by diffusive heat conduction; and (3) some convective processes, whose characteristics are not fully known, add to the heat transfer. The raw data are presented, and the analysis approach is given.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-64735
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  • 66
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    Preliminary measurements on heat balance in pneumatic tires (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A variety of tests was undertaken to determine the nature of heat generation associated with a pneumatic tire operating under various conditions. Tests were conducted to determine the magnitude and distribution of internally generated heat caused by hysteresis in the rubber and ply fabric in an automobile tire operating under conditions of load, pressure, and velocity representative of normal operating conditions. These included tests at various yaw angles and tests with braking applied. In other tests, temperature sensors were mounted on a road to measure the effect of a tire rolling over and an attempt was made to deduce the magnitude and nature of interfacial friction from the resulting information. In addition, tests were performed using the scratch plate technique to determine the nature of the motion between the tire and road. Finally, a model tire was tested on a roadwheel, the surface covering which could be changed, and an optical pyrometer was used to measure rubber surface temperatures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-121239 , REPT-036390-2-T
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  • 67
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    Ablation article and method (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An ablation article, such as a conical heat shield, having an ablating surface is provided with at least one discrete area of at least one seed material, such as aluminum. When subjected to ablation conditions, the seed material is ablated. Radiation emanating from the ablated seed material is detected to analyze ablation effects without disturbing the ablation surface. By providing different seed materials having different radiation characteristics, the ablating effects on various areas of the ablating surface can be analyzed under any prevailing ablation conditions. The ablating article can be provided with means for detecting the radiation characteristics of the ablated seed material to provide a self-contained analysis unit.
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  • 68
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    Disconnect unit (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A squib-actuated disconnect is characterized by an expandable collet axially extended from a first tension member for receiving in locking engagement a protuberance axially extended from a second tension member. A gas-driven retainer of an annular configuration is also locked in for supporting the collet in locking engagement with the protuberance. The protuberance is axially displaced in response to a firing of an associated squib for thus accommodating a disengagement of the protuberance and the collet.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 69
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    Simulation experiments using hydrogen/oxygen gas mixtures in a high pressure detonation tube (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulation of rocket plumes and reentry aerothermodynamics using oxygen/hydrogen combustion products
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-128955 , MSC-05836
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  • 70
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    Effect of fuel vapor concentrations on combustor emissions and performance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Effects of fuel vaporization on the exhaust emission levels of oxides of nitrogen, carbon monoxide, total hydrocarbons, and smoke number were obtained in an experimental turbojet combustor segment. Two different fuel injectors were used in which liquid ASTM A-1 jet fuel and vapor propane fuel were independently controlled to simulate varying degrees of vaporization. Tests were conducted over a range of inlet-air temperatures from 478 to 700 K, pressures from 4 to 20 atm, and combustor reference velocities from 15.3 to 27.4 m/sec. Converting from liquid to complete vapor fuel resulted in oxides of nitrogen reductions of as much as 22 percent and smoke number reductions up to 51 percent. Supplement data are also presented on flame emissivity, flame temperature, and primary-zone liner wall temperatures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2800 , E-7336
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  • 71
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    Effect of pressure on tangential-injection film cooling in a combustor exhaust stream (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A tangential-injection film cooled test section was placed in the exhaust stream of a high pressure combustor. Film cooling data were taken at pressure of 1, 10, and 20 atmospheres. The film cooling effectiveness was found to be independent of pressure. The data were correlated adequately by a turbulent-mixing film cooling correlation with a turbulent-mixing coefficient of 0.05 + or - 0.02.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2809 , E-7388
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  • 72
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    Engine investigation of an impingement-cooled turbine rotor blade (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimentally determined heat transfer characteristics of an impingement-cooled turbine rotor blade are reported. The test results are compared with those obtained for three convection-cooled turbine blades tested in the same facility in addition to impingement correlations found in literature.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2791 , E-7313
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  • 73
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    Improved multiple-shot gun for use as a combustion stability rating device (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A program was conducted to develop and experimentally evaluate an improved version of a modified machine gun for use as a device for rating the relative combustion stability of various rocket combustors. Following the results of a previous study involving a caliber .30 machine gun, a caliber .50 machine gun was modified in order to extend the charge-size range of the device. Nitrocellulose charge sizes ranging from 1.004 to 9.720 grams were fired at rates up to four shots per second. Shock pressures up to 25,512 kN/sq m were measured near the end of a shortened gun barrel. A minimal resistance type of check valve permitted the gun to fire into pressurized regions; back pressures up to 3448 kN/sq m abs were tested. The final modified assembly was evaluated during combustion stability tests on rocket combustors burning a FLOX-methane propellant combination.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-2792 , E-7287
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  • 74
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    Inherent redundacy electric heater (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A cross-wound electrical heater comprising two resistance coils wound together with opposite pitches electrically connected at their crossing points, is reported. Each element is supplied by a separate power supply of the same magnitude, and each power supply is isolated from reverse currents by a diode. Failure of one of the windings results in only a moderate change in output power.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 75
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    Explosives and pyrotechnic propellants for use in long term deep space missions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Explosives and pyrotechnic propellant materials which will withstand heat sterilization cycling at 125 C and ten year deep space aging under 10 to the minus 6th power torr and 66 C have been selected. The selection was accomplished through a detailed literature survey and an analytical evaluation of the physicochemical properties of the materials. The chemical components of the electroexplosive devices used in U.S. missiles and spacecraft were categorized into primary explosives, secondary explosives, and propellant ingredients. Kinetic data on such parameters as thermal decomposition and sublimation were obtained for these materials and used as a basis for the ten year life prediction. From these experimental data and some analytical calculations, a listing of candidate materials for deep space missions was made.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132373
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  • 76
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    Some analyses of the chemistry and diffusion of SST exhaust materials during phase 3 of the wake period (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: In the generally stably stratified lower stratosphere, SST exhaust plumes could spend a significant length of time in a relatively undispersed state. This effort has utilized invariant modeling techniques to simulate the separate and combined effects of atmospheric turbulence, turbulent diffusion, and chemical reactions of SST exhaust materials in the lower stratosphere. The primary results to date are: (1) The combination of relatively slow diffusive mixing and rapid chemical reactions during the Phase III wake period minimizes the effect of SST exhausts on O3 depletion by the so-called NOx catalytic cycle. While the SST-produced NO is substantially above background concentrations, it appears diffusive mixing of NO and O3 is simply too slow to produce the O3 depletions originally proposed. (2) The time required to dilute the SST exhaust plume may be a significant fraction of the total time these materials are resident in the lower stratosphere. If this is the case, then prior estimates of the environmental impact of these materials must be revised significantly downward.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132323 , ARAP-199
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  • 77
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    Controlled oscillator system with a time dependent output frequency (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A controlled oscillator system is presented for providing an output with a frequency which changes with respect to time and with a phase which is within established phase error limits. The system includes a frequency synthesizer with a symmetrical search oscillator, capable of tuning the output with a range of + or - 100 Hz about any fixed frequency to which the synthesizer is set. For a tuning range of 200 Hz (+ or - 100 Hz) an expanded search oscillator output of a frequency range of 4 MHz (from 1 MHz to 5 MHz) is provided. A counter counts continuously the expanded output cycles and at each of fixed sampling intervals, for every 0.1 second, the count or number accumulated in the counter is read out. The sample number is compared with a theoretical number which should be present in the counter at the particular sampling instant for proper synthesizer's output frequency and phase.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 78
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    Thermokinetics and combustion phenomena in nonflowing gaseous systems - An invited review. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The current status of our understanding of combustion phenomena observed in nonflowing premixed gaseous systems is reviewed. The phenomena include slow oxidation, explosion, multiple ignition, oscillatory oxidation, as well as photolytic phenomena. Detailed experimental data on each of these phenomena are given, and analytical methods of analyzing them are outlined. The correlation between theory and experiment is studied for several special cases.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Combustion and Flame; 21; Oct. 197
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  • 79
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    Unsteady, combined radiation and conduction in an absorbing, scattering, and emitting medium. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The transient cooldown of a gray, absorbing, isotropic scattering, emitting, and conducting medium bounded by gray, diffusely emitting and reflecting parallel plates is considered. Numerical solutions are obtained for the initial boundary-value problem with a discontinuous decrease in temperature at one boundary. The quasi-steady equation of radiative transfer is solved using Gaussian quadrature and a matrix eigenvector technique together with explicit numerical solution of the unsteady energy equation. Temperature and energy flux distributions are presented for variations of optical thickness, boundary emissivity, albedo, and conduction-radiation parameter.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 73-HT-J
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  • 80
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    Leidenfrost temperature - Its correlation for liquid metals, cryogens, hydrocarbons, and water. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 73-HT-F
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  • 81
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    An experimental-analytical method to study steady spray combustion. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Description of a method for determining the local parameters of the gas mixture resulting from the combustion of sprayed fuel in a gaseous oxidizer. The method is based on the measurement of local static pressures in the gas mixture and does not require the knowledge of the droplet distribution function, drag, and vaporization characteristics. A set of equations with substituted local pressure values is used for calculations. Application of the method is demonstrated on a liquid oxygen-ethanol rocket fuel.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 10; June 197
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  • 82
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    Sampling nitric oxide from combustion gases. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Experimental study of several sampling tube and probe material compositions and designs aimed at preventing nitric oxide reduction when sampling nitric oxide from combustion gases. A 250,000 Btu/h furnace fired with technical grade methane was used for testing the sampling probes over a wide range of air-fuel mixtures. The results obtained include the finding that the use of stainless steel in probes creates inaccuracies in near-stoichiometric and fuel-rich sampling in hydrocarbon flames. For very fuel-rich flames, water cooling is needed even in quartz probes to prevent significant reduction of nitric oxide.-
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Combustion and Flame; 20; June 197
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  • 83
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    Test of statistical models for gases with and without internal energy states. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The problem of nonlinear rarefied Couette flow with heat transfer has been studied for both monatomic and diatomic gases using the Boltzmann equation with the Bhatnagar-Gross-Krook type models as the governing equation and the method of discrete ordinates as a tool. The calculated results have been compared with the existing experimental data in order to test the accuracy and the applicability of the statistical models for this one-dimensional problem. The calculated density results are found to be in good agreement with available experimental data; the calculated heat flux solution for the linear case is found to always be lower than the experimental data of Teagan and Springer. The comparisons made here indicate that the statistical models are indeed reasonably accurate so that their use is justified in the type of problems investigated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 16; Apr. 197
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  • 84
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    Experimental study of shock-wave reflection from a thermally accommodating wall. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Shock-tube experiments have been conducted to study the nonequilibrium gas-surface interaction which occurs when a thick shock wave in argon reflects from a coplanar, heat-conducting wall. Fast-response instrumentation was used to monitor variations in temperature and normal stress on the surface of the shock-tube end wall during and immediately following reflection of the incident shock wave. The laboratory observations are compared with computer predictions obtained by Deiwert using the direct-simulation Monte Carlo method, and excellent agreement is obtained when a suitable average thermal accommodation coefficient is chosen for the wall surface.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 16; Mar. 197
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  • 85
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    Mixing-controlled supersonic combustion. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The technology of supersonic combustion and its practical significance for hypersonic flight are reviewed. It is shown that this technology makes possible a good qualitative and quantitative understanding of the physical phenomena related to the process of supersonic combustion. Some of the more important, summarized aspects of this technology include the physical description of the supersonic combustion flame, the chemical reaction rates and the diffusion process involved, the interaction between combustion and fluid dynamics, and the mathematical methods of supersonic combustion analysis.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 86
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    Experiments in gasdynamics of explosions. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Various topics concerning recent accomplishments in experimental studies of gasdynamics of explosions are reviewed. Detonations, shocks, and blast waves form these topics. The most important feature of current studies is the particular attention paid to transient processes and the concomitant progress made in the development of novel experimental means for the study of such processes. The most exciting prospects for the future are associated with possibilities of exploiting knowledge of explosion phenomena for the development of such interesting devices as the gasdynamic laser and the apparatus based on the use of lasers to achieve controlled thermonuclear reaction.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-764339 , AFOSR-73-1299TR
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  • 87
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    An approximate analysis of the diffusing flow in a self-controlled heat pipe. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Constant-density two-dimensional axisymmetric equations are presented for the diffusing flow of a class of self-controlled heat pipes. The analysis is restricted to the vapor space. Condensation of the vapor is related to its mass fraction at the wall by the gas kinetic formula. The Karman-Pohlhausen integral method is applied to obtain approximate solutions. Solutions are presented for a water heat pipe with neon control gas.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 72-HT-M
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  • 88
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    Mach stem structure in exothermic systems. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Incident waves having grossly similar characteristics were obtained by passing a shock wave over a ramp mounted on the divergent part of a convergent-divergent nozzle. The range of triple point parameters in both the naturally occurring detonative Mach stems and those generated in the ramp experiments compared favorably, but some differences were observed in the triple point trajectories and the decay rates of the lead waves. Whereas the lead waves in detonations have been found to decay at rates between those of planar and cylindrical blast waves, the decay observed in the ramp experiments was more like that of planar blast waves. The dominant factor in determining a triple point trajectory was found to be the orientation of the lead wave at the triple point. Comparison of reactive and nonreactive cases indicated a faster rate of decay of the lead wave and a steeper triple point trajectory for the reactive cases than for the nonreactive ones. Also, a sensitivity of the trajectory to initial pressure was observed in the former, although none was present in the nonreactive cases.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Combustion and Flame; 20; Feb. 197
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  • 89
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    Experimental determination of three-dimensional liquid rocket nozzle admittances. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: The three-dimensional nozzle admittance, an important parameter in combustion instability studies, was experimentally measured for several nozzle configurations. The admittance values were obtained using a modification of the classical impedance tube technique. The modified impedance tube method measures the admittance of a duct termination in the presence of one-dimensional mean flow and three-dimensional oscillations. Values of the nozzle admittance were obtained from pressure amplitude measurements taken at discrete points along the length of the tube. To determine the effects of nozzle geometry, nozzles were tested with half-angles of 15, 30, and 45 deg and entrance Mach numbers of 0.08, 0.16, and 0.20. The admittance results are presented as functions of nondimensional frequency for mixed first tangential-longitudinal modes. These results are compared with available theoretical predictions, and good agreement between theory and experiment is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA Journal; 11; Mar. 197
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  • 90
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    Spacecraft thermal environments. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Description: Definitions are given for spacecraft-surface thermal environment characteristics. Lumped-parameter thermal network modeling techniques are derived for spacecraft thermal environment analysis. The application of these techniques to thermal/vacuum testing is described. A major computer program required by these techniques is outlined. It is noted that this approach has been used to determine thermal environments for the Skylab ATM.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 10; Jan. 197
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  • 91
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    Variable properties laminar gas flow heat transfer in the entry region of parallel porous plates. (1973)
    In:  Other Sources
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    Publication Date: 2019-06-27
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AD-759455 , International Journal of Heat and Mass Transfer; 16; Mar. 197
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  • 92
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    Prediction of fluctuating pressure environments associated with plume-induced separated flow fields (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The separated flow environment induced by underexpanded rocket plumes during boost phase of rocket vehicles has been investigated. A simple semi-empirical model for predicting the extent of separation was developed. This model offers considerable computational economy as compared to other schemes reported in the literature, and has been shown to be in good agreement with limited flight data. The unsteady pressure field in plume-induced separated regions was investigated. It was found that fluctuations differed from those for a rigid flare only at low frequencies. The major difference between plume-induced separation and flare-induced separation was shown to be an increase in shock oscillation distance for the plume case. The prediction schemes were applied to PRR shuttle launch configuration. It was found that fluctuating pressures from plume-induced separation are not as severe as for other fluctuating environments at the critical flight condition of maximum dynamic pressure.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-124346 , WR-73-3
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  • 93
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    An efficient numerical technique for calculating thermal spreading resistance (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a thermal spreading resistance data generation technique study are reported. The method developed is discussed in detail, illustrative examples given, and the resulting computer program is included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-124312
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  • 94
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    Design and testing of a passive, feedback-controlled, variable conductance heat pipe (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A passive feedback system, which stabilizes the heat source temperature (T sub s) of a gas loaded heat pipe, was designed and tested. The control of T sub s is accomplished by an auxiliary liquid that senses the heat source and actuates a metal bellows system due to the liquid's thermal expansion. The movement of the bellows varies the gas reservoir volume and leads to a corresponding change of the condensation area of the heat pipe. With methanol as the heat pipe working fluid and perfluoro-n-pentane as the auxiliary liquid, the control capability was found to be T sub s = 31.5 + or - 1.5 C in a power range from 3 to 30 W, compared to T sub s = 33 + or - 3 C with methanol as auxiliary liquid. The change in T sub s was 35 + or - 5.5 C with the bellows held in the closed position.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-62293
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  • 95
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    Flow through a wire-form transpiration-cooled vane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of recent research to develop techniques for analyzing coolant flow in transpiration-cooled vanes are summarized. Flow characteristics of the wire-form porous material are correlated; the effects on the flow characteristics of oxidation, coolant temperature, gas crossflow, and airfoil curvature are evaluated. An analytical method is presented for predicting coolant flows and pressures in a strut-supported vane.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7341 , E-7385
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  • 96
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    ATS-F radiant cooler contamination test in a hydrazine thruster exhaust (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test was conducted under simulated space conditions to determine the potential thermal degradation of the ATS-F radiant cooler from any contaminants generated by a 0.44-N(0.1-lbf) hydrazine thruster. The radiant cooler, a 0.44-N(0.1-lbf)hydrazine engine, and an aluminum plate simulating the satellite interface were assembled to simulate their flight configuration. The cooler was provided with platinum sensors for measuring temperature, and its surfaces were instrumented with six quartz crystal microbalance units (QCM) to measure contaminant mass deposits. The complete assembly was tested in the molecular sink vacuum facility (Molsink) at the Jet Propulsion Laboratory. This was the first time that a radiant cooler and a hydrazine engine were tested together in a very-high-vacuum space simulator, and this test was the first successful measurement of detectable deposits from hydrazine rocket engine plumes in a high vacuum. The engine was subjected to an accelerated duty cycle of 1 pulse/min, and after 2-hr of operation, the QCMs began to shift in frequency. The tests continued for several days and, although there was considerable activity in the QCMs, the cooler never experienced thermal degradation.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132988 , JPL-TM-33-592
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    Thermodynamic properties of UF sub 6 measured with a ballistic piston compressor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: From experiments performed with a ballistic piston compressor, certain thermodynamic properties of uranium hexafluoride were investigated. Difficulties presented by the nonideal processes encountered in ballistic compressors are discussed and a computer code BCCC (Ballistic Compressor Computer Code) is developed to analyze the experimental data. The BCCC unfolds the thermodynamic properties of uranium hexafluoride from the helium-uranium hexafluoride mixture used as the test gas in the ballistic compressor. The thermodynamic properties deduced include the specific heat at constant volume, the ratio of specific heats for UF6, and the viscous coupling constant of helium-uranium hexafluoride mixtures.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132051
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  • 98
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    Heat transfer coefficients of dilute flowing gas-solids suspensions (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer coefficients of air-glass, argon-glass, and argon-aluminum suspensions were measured in horizontal and vertical tubes. The glass, 21.6 and 36.0 micron diameter particles, was suspended at gas Reynolds numbers between 11,000 and 21,000 and loading ratios between 0 and 2.5. The presence of particles generally reduced the heat transfer coefficient. The circulation of aluminum powder in the 0.870 inch diameter closed loop system produced tenacious deposits on protuberances into the stream. In the vertical test section, the Nusselt number reduction was attributed to viscous sublayer thickening; in the horizontal test section to particle deposition.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-2266
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  • 99
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    Transient boiling heat transfer in saturated liquid nitrogen and F113 at standard and zero gravity (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Transient and steady state nucleate boiling in saturated LN2 and F113 at standard and near zero gravity conditions were investigated for the horizontal up, vertical and horizontal down orientations of the heating surface. Two distinct regimes of heat transfer mechanisms were observed during the interval from the step increase of power input to the onset of nucleate boiling: the conduction and convection dominated regimes. The time duration in each regime was considerably shorter with LN2 than with F113, and decreased as heat flux increased, as gravity was reduced, and as the orientation was changed from horizontal up to horizontal down. In transient boiling, boiling initiates at a single point following the step increase in power, and then spreads over the surface. The delay time for the inception of boiling at the first site, and the velocity of spread of boiling varies depending upon the heat flux, orientation, body force, surface roughness and liquid properties, and are a consequence of changes in boundary layer temperature levels associated with changes in natural convection. Following the step increase in power input, surface temperature overshoot and undershoot occur before the steady state boiling temperature level is established.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-120202 , REPT-074610-52-F
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  • 100
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    Variable conductance heat pipe technology (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Research and development programs in variable conductance heat pipe technology were conducted. The treatment has been comprehensive, involving theoretical and/or experimental studies in hydrostatics, hydrodynamics, heat transfer into and out of the pipe, fluid selection, and materials compatibility, in addition to the principal subject of variable conductance control techniques. Efforts were not limited to analytical work and laboratory experimentation, but extended to the development, fabrication and test of spacecraft hardware, culminating in the successful flight of the Ames Heat Pipe Experiment on the OAO-C spacecraft.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114686 , RR-4
    Format: application/pdf
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