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  • THERMODYNAMICS AND COMBUSTION
  • 1970-1974  (154)
  • 1974  (154)
  • 1
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    Heat Transfer and Thermodynamics: a Compilation (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A compilation is presented for the dissemination of information on technological developments which have potential utility outside the aerospace and nuclear communities. Studies include theories and mechanical considerations in the transfer of heat and the thermodynamic properties of matter and the causes and effects of certain interactions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-5959(01)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Thermal-Structural Evaluation of TD Ni-20Cr Thermal Protection System Panels (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The results of a thermal-structural test program to verify the performance of a metallic/radiative Thermal Protection System (TPS) under reentry conditions are presented. This TPS panel is suitable for multiple reentry, high L/D space vehicles, such as the NASA space shuttle, having surface temperatures up to 1200 C (2200 F). The TPS panel tested consists of a corrugation-stiffened, beaded-skin TD Ni-20Cr metallic heat shield backed by a flexible fibrous quartz and radiative shield insulative system. Test conditions simulated the critical heating and aerodynamic pressure environments expected during 100 repeated missions of a reentry vehicle. Temperatures were measured during each reentry cycle; heat-shield flatness surveys to measure permanent set of the metallic components were made every 10 cycles. The TPS panel, in spite of localized surface failures, performed its designated function.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-132487
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Conformal mapping technique for two-dimensional porous media and jet impingement heat transfer (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Transpiration cooling and liquid metals both provide highly effective heat transfer. Using Darcy's law in porous media and the inviscid approximation for liquid metals, the local fluid velocity in these flows equals the gradient of a potential. The energy equation and flow region are simplified when transformed into potential plane coordinates. In these coordinates, the present problems are reduced to heat conduction solutions which are mapped into the physical geometry. Results are obtained for a porous region with simultaneously prescribed surface temperature and heat flux, heat transfer in a two-dimensional porous bed, and heat transfer for two liquid metal slot jets impinging on a heated plate.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Heat Transfer Conference; Sept. 3-7, 1974; Tokyo; Japan
    Format: text
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  • 4
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    An exact solution of a simplified two-phase plume model (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An exact solution of a simplified two-phase, gas-particle, rocket exhaust plume model is presented. It may be used to make the upper-bound estimation of the heat flux and pressure loads due to particle impingement on the objects existing in the rocket exhaust plume. By including the correction factors to be determined experimentally, the present technique will provide realistic data concerning the heat and aerodynamic loads on these objects for design purposes. Excellent agreement in trend between the best available computer solution and the present exact solution is shown.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Southeastern Conference on Theoretical and Applied Mechanics; Mar 21, 1974 - Mar 22, 1974; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Cryogenic and low temperature heat pipe/cooler studies for spacecraft application (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The prime purpose of the present work is to examine cryogenic heat pipe/cooler feasibility in the 80 to 100 K temperature range and in the regimes of operation required for NASA spacecraft. Present requirements within these regimes are (1) cooling load of less than 1 to 2 watt per cooler, (2) small detector/heat pipe interface area, and (3) high system reliability and long lifetime operations. The cooling capacity of practical radiant coolers is very low in this temperature range, and very temperature sensitive. Detector performance is also strongly dependent on temperatures in this regime. It is, therefore important to understand the interplay of the heat pipe and its effects on overall system performance.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-753 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 6
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    Heat Transfer and Fluid Mechanics Institute, 24th, Oregon State University, Corvallis, Ore., June 12-14, 1974, Proceedings (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Recent theoretical and experimental studies in heat transfer and fluid mechanics, including some environmental protection investigations, are presented in a number of papers. Some of the topics covered include condensation heat transfer, a model of turbulent momentum and heat transfer at points of separation and reattachment, an explicit scheme for calculations of confined turbulent flows with heat transfer, heat transfer effects on a delta wing in subsonic flow, fluid mechanics of ocean outfalls, thermal plumes from industrial cooling water, a photochemical air pollution model for the Los Angeles air basin, and a turbulence model of diurnal variations in the planetary boundary layer. Individual items are announced in this issue.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Heat Transfer and Fluid Mechanics Institute; Jun 12, 1974 - Jun 14, 1974; Corvallis, OR; US
    Format: text
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  • 7
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    An approximate inviscid radiating flow-field analysis for sphere-cone Venusian entry vehicles (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computational method based on the earlier work of one of the authors has been improved and modified to provide an accurate and rapid prediction of the radiating flow about blunt conical probes entering the atmosphere of Venus. Special features include a more general approximate equation of state, a more rapidly converging iteration scheme, a 38-step absorption coefficient model for a Venus atmosphere gas mixture model, and a shock-shape formula which yields a computed body shape in excellent agreement with the desired body. The method was used to calculate distributions of radiative heating for a large spherically blunted conical probe vehicle (1.219 m base diameter) and for three small spherically blunted conical probe vehicles (0.724 m base diameter). Solutions obtained with the presently developed approximate method required short computing times of the order of 1 to 3 minutes for each complete solution and gave agreements of 10% to 15% with the more exact predictions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-758 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 8
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    Volume reflecting heat shields for entry into the giant planet atmospheres (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The performance of a volume reflecting or backscattering silica heat shield is examined for an entry probe into the severe radiative environments of Saturn, Uranus, and Jupiter. The governing equations for the material response are solved numerically and include the effects of temperature-dependent thermal properties, temperature- and wavelength-dependent radiative properties, and surface recession caused by thermochemical ablation. The influence of the scattering properties on backface temperature is examined, and results are presented which show the required heat-shield thickness for the entry trajectories selected.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-669 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 9
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    Temperature difference-dependent interface thermal resistance of ring-stiffened, corrugated spacecraft shrouds (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-729 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
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  • 10
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    Parametric performance of extruded axial grooved heat pipes from 100 to 300 K (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Extensive performance data derived from tests with an aluminum axial grooved extruded heat pipe is presented for oxygen, methane, ethane, and ammonia as working fluids. The effects of operating temperature, fluid inventory, heat flux, and elevation on the transport capability and the evaporator and condenser film coefficients are measured and compared to theory. The data correlation indicates that, in addition to the viscous pressure drop of the fluid, a vapor induced liquid pressure drop must be taken into account at temperatures near or below the normal boiling point of the fluid. Methane, ethane, and ammonia are all suitable working fluids for this groove geometry; however, oxygen, because of its low static height, is at best marginal in the 100-120 K range.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: AIAA PAPER 74-724 , Thermophysics and Heat Transfer Conference; Jul 15, 1974 - Jul 17, 1974; Boston, MA
    Format: text
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