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  • THERMODYNAMICS AND COMBUSTION  (48)
  • LUNAR AND PLANETARY EXPLORATION
  • ASTROPHYSICS
  • 1975-1979
  • 1970-1974  (49)
  • 1972  (49)
Collection
Keywords
Years
  • 1975-1979
  • 1970-1974  (49)
Year
  • 1
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    Hot-gas-side heat transfer with and without film cooling on a simulated nuclear rocket thrust chamber using H2-O2 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Heat-transfer coefficients were obtained on a thrust chamber which simulated the geometry of the NERVA nuclear rocket. The tests were performed with and without peripheral film cooling over a chamber pressure range of 1.05 million to 5.84 million newtons per square meter (153 to 847 psia). With no film cooling, the overall axial variation in the value of the correlation coefficient C of the equation (Stanton)* (Prandtl)* to the 0.7ths power = C(Reynolds)* to the -0.2ths power, where * indicates the reference enthalpy condition, was reduced 66 percent when the local diameter in the Reynolds number was replaced by the axial distance from the injector face. The average peak values of C were reduced 25 percent with 2 and 3.75 percent cooling and 50 percent with 7.5 percent cooling.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-6638 , E-6553
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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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
  • 3
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    Oxidation protected carbon-carbon (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Pyrolized carbon-carbon has one unique advantage over other materials that makes its application to the space shuttle thermal protection system very attractive. This unique characteristic is the increase in material strength and modulus with increase in temperature up to about 2500 K (4040 F). Offsetting this unique advantage are disadvantages which include brittleness, high cost, and the tendency of the material to react with oxygen, particularly at high temperatures. The development of an oxidation inhibitor for the material and the definition of fabrication processes for selected full-scale components are considered.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 335-372
    Format: text
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  • 4
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    Effects of roughness on heating and boundary-layer transition. Part 1: Effects of simulated panel joints on boundary-layer transition (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effects of distributed roughness, arising from space shuttle orbiter panel joints, on boundary layer transition are investigated. The North American Rockwell 134B delta wing shuttle configuration was used for the study. Results show: (1) Premature boundary layer transition occurred in models having simulated heat shield panels with rased joints. (2) Laminar flow was maintained with slot type panel joint models to a Reynolds number twice that at which transition occurred in raised joints. (3) Significant increases in peak surface temperature and the time during which turbulent flow occurs may result from distributed roughness of heat shield panel joints. (4) Laminar and turbulent heating levels were predicted within available theories. (5) A complex interference between the wing and fuselage flow was observed in the delta wing model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 375-394
    Format: text
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  • 5
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    Oscillation effects upon film boiling from a sphere. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Heat transfer rates from a silver-plated copper sphere, 0.75 in. in diameter, were studied by high speed photography during oscillations of the sphere in saturated liquid nitrogen and Freon-11. The oscillation frequencies ranged from zero to 13 Hz, and the amplitude-to-diameter ratio varied from zero to 2.67. The sphere was supported by a thin-walled stainless steel tube and carried a thermocouple attached near the lower stagnation point. A Fastax WF-3 16mm movie camera was used at about 2000 frames/sec. The differences in the vapor removal process at lower and higher oscillation frequencies are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
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  • 6
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    Nonequilibrium and Equilibrium Radiation to the Space Tug from the Shock Layer (1972)
    In:  CASI
    Details
    Publication Date: 2014-09-09
    Description: Preliminary estimates of the thermal radiation heat transfer to an aerobraking space tug are presented. The tug is descending from a geosynchronous orbit to a low earth orbit on one or more passes through the atmosphere. For the flight regime of the tug, between a velocity of 22,000 ft./sec. and 34,000 ft./sec. with an altitude between 220,000 ft. and 340,000 ft., the nonequilibrium radiation can be more than 1,000 times larger than the value of the equilibrium radiation. Therefore, an analysis of the radiative heating for these altitude must include the nonequilibrium radiation from the shock layer.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Auburn Univ. The NASA-ASEE Summer Fac. Fellowship Program; p 229-278
    Format: text
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  • 7
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    Studies of oscillatory combustion and fuel vaporization (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Research projects involving oscillatory combustion and fuel vaporization are reported. Comparisons of experimental and theoretical droplet vaporization histories under ambient conditions such that the droplet may approach its thermodynamic critical point are presented. Experimental data on instantaneous heat transfer from a gas to a solid surface under conditions of oscillatory pressure with comparisons to an unsteady one-dimensional model are analyzed. Droplet size and velocity distribution in a spray as obtained by use of a double flash fluorescent method were investigated.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-CR-120974
    Format: application/pdf
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  • 8
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    Effective thermal conductivities of four metal ceramic composite coatings in hydrogen-oxygen rocket firings (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the effective conductivities of four plasma-arc-sprayed, metal-ceramic gradated coatings on hydrogen-oxygen thrust chambers. The effective thermal conductivities were not a function of pressure or oxidant-to-fuel ratio. The various materials that made up these composites do not seem to affect the thermal conductivity values as much as the differences in the thermal conductivities of the parent materials would lead one to expect. Contact resistance evolving from the spraying process seems to be the controlling factor. The thermal conductivities of all the composites tested fell in the range of 0.75 to 7.5 watts per meter kelvin.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-TN-D-7055 , E-7035
    Format: application/pdf
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  • 9
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    Correlation of liquid-film cooling mass transfer data. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An empirical correlation proposed by Gater and Ecuyer (1970) for liquid-film cooling mass transfer, accounting for film roughness and entrainment effects, is extended to include liquid films of arbitrary length. A favorable comparison between the predicted results and the experimental data of Kinney et al. (1952) and Emmons and Warner (1964) shows the utility of the mass transfer correlation for predictions over a wide range of experimental parameters.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: International Journal of Heat and Mass Transfer; 15; Oct. 197
    Format: text
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  • 10
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    Partially ionized gas flow and heat transfer in the separation, reattachment, and redevelopment regions downstream of an abrupt circular channel expansion. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Heat transfer and pressure measurements obtained in the separation, reattachment, and redevelopment regions along a tube and nozzle located downstream of an abrupt channel expansion are presented for a very high enthalpy flow of argon. The ionization energy fraction extended up to 0.6 at the tube inlet just downstream of the arc heater. Reattachment resulted from the growth of an instability in the vortex sheet-like shear layer between the central jet that discharged into the tube and the reverse flow along the wall at the lower Reynolds numbers, as indicated by water flow visualization studies which were found to dynamically model the high-temperature gas flow. A reasonably good prediction of the heat transfer in the reattachment region where the highest heat transfer occurred and in the redevelopment region downstream can be made by using existing laminar boundary layer theory for a partially ionized gas. In the experiments as much as 90 per cent of the inlet energy was lost by heat transfer to the tube and the nozzle wall.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ASME PAPER 71-HT-DD
    Format: text
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