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  • THERMODYNAMICS AND COMBUSTION  (49)
  • 2020-2023
  • 2010-2014
  • 1970-1974  (49)
  • 1965-1969
  • 2020
  • 1972  (49)
Collection
Keywords
Years
  • 2020-2023
  • 2010-2014
  • 1970-1974  (49)
  • 1965-1969
Year
  • 1
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Nonlinear least squares - An aid to thermal property determination (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    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; techniques; the method of Peckham was the most efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TM-X-58092 , MSC-07048
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The aerothermodynamic environment of the Apollo command module during superorbital entry (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerothermodynamic measurements were obtained on two Apollo spacecraft during atmospheric entry at near-lunar-return velocities. Histories of measured pressure and of convective and radiative heating rates are compared with theoretical predictions and with wind-tunnel results. The comparisons show that pressures measured in the wind tunnel correspond to those measured in the flight environment of the entry face. Unexplained low pressures were obtained on the conical section. Measured radiative heating rates agree with predictions calculated for both visible and infrared radiation. Good agreement was found between convective heating rates measured in flight and predictions obtained by using cold wall theory adjusted for mass injection from the ablator.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-6792 , MSC-S-267
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Theory and design of variable conductance heat pipes: Steady state and transient performance (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat pipe technology pertinent to the design and application of self-controlled, variable conductance heat pipes for spacecraft thermal control is discussed. Investigations were conducted to: (1) provide additional confidence in existing design tools, (2) to generate new design tools, and (3) to develop superior variable conductance heat pipe designs. A computer program for designing and predicting the performance of the heat pipe systems was developed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-114530 , REPT-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Results of a comprehensive program for analysis of thermal radiative properties. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An extensive program has been developed to identify, collect, extract, analyze, and disseminate thermal radiative property data on materials of use to the aerospace endeavors under conditions likely to exist in their application. The properties examined include thermal emittance, reflectance, absorptance, and transmittance. Reference is made to the coverage of the results which is organized in three major volumes, representing the most comprehensive treatment on this subject matter.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 72-307 , American Institute of Aeronautics and Astronautics, Thermophysics Conference; Apr 10, 1972 - Apr 12, 1972; San Antonio, TX
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Diffusion freezeout in gas-loaded heat pipes. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Experimental diffusion freezeout rates in a gas loaded heat pipe are presented and compared with predictions of an analysis and computer program published earlier. The experimental approach was to pivot a heat pipe on knife edges and use an analytical mass balance to measure the rate of mass migration within the pipe. Diffusion freezeout rates in a water heat pipe were measured as a function of the condenser sink temperature and the condenser-to-sink thermal conductance. Measured rates varied between 19 and 270 mg/hr and yielded 64 to 99 percent agreement with predicted values. These results indicated that the analysis and computer program for predicting the behavior of gas loaded heat pipes are useful tools for designing such systems.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 72-WA/HT-33 , Winter Annual Meeting of the American Society of Mechanical Engineers; Nov 26, 1972 - Nov 30, 1972; New York, NY
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Ablator manufacturing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Studies are being conducted to determine how manufacturing-induced defects affect the performance of ablative heat shields. If commonly occurring defects do not affect material performance, simpler manufacturing techniques can be used, quality control requirements can be relaxed, repair and rework operations can be held to a minimum, and thus the total manufacturing cost can be reduced.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 475-504
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Reusable surface insulation materials research and development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Reusable surface insulation is considered a prime candidate for heat shielding large areas of the space shuttle vehicle. The composition and fabrication of RSI materials are discussed, followed by evolution of RSI and current problems, physical and thermal properties, arc plasma test data and results, and material improvement research. Finally, a summary of RSI technology status is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 373-433
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thermal protection system trade studies on ablators and reuseable surface insulation (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 303-334
    Format: text
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  • 10
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    An assessment of radiative metallic thermal protection systems for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The metallic thermal protection system technology program for the space shuttle is reviewed for the areas of environmental uncertainties, materials data base, TPS design concepts and heat-shield panel configurations, testing and evaluation of materials, panels, and complete systems.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 267-302
    Format: text
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    NASA TECHNICAL REPORTS
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