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  • THERMODYNAMICS AND COMBUSTION  (44)
  • 1970-1974  (44)
  • 1935-1939
  • 1973  (44)
  • 1
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    Nonlinear least squares - An aid to thermal property determination. (1973)
    In:  Other Sources
    Details
    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
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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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
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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    An experimental investigation of some heat transfer characteristics on an orbiter/HO-tank/SRM Space Shuttle configurations, freestream Mach number equal to 8.0. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 73-92 , Aerospace Sciences Meeting; Jan 10, 1973 - Jan 12, 1973; Washington, DC
    Format: text
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  • 5
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    Experiments on radiatively driven harmonic acoustic waves in a confined gas. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Measurements are presented of the acoustic pressure resulting from the periodic absorption and emission of radiative energy by an infrared-active gas contained in a closed, cylindrical tube. The acoustic waves are generated by means of an external, sinusoidally time-modulated blackbody source. The pressure measurements are for both resonant and nonresonant conditions at acoustic frequencies from about 60 to 600 Hz. Comparison of the measurements with predictions shows that the response is due primarily to the modified-classical acoustic wave, but that a small contribution from the so-called radiation-induced wave can be measured in certain of the tests. Strong effects of vibrational nonequilibrium, similar to those observed previously in spectrophone studies, were found in some of the tests.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Physics of Fluids; 16; Aug. 197
    Format: text
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  • 6
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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
    Format: text
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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
    Details
    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
    Format: text
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  • 8
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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
    Format: application/pdf
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  • 9
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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
    Format: application/pdf
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  • 10
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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
    Format: application/pdf
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