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  • Fluid Mechanics and Thermodynamics
  • 1985-1989
  • 1960-1964  (4)
  • 1945-1949
  • 1964  (4)
Collection
Years
  • 1985-1989
  • 1960-1964  (4)
  • 1945-1949
Year
  • 1
    Publication Date: 2019-05-21
    Description: Large-deflection theory is used to compute buckling loads of simply supported initially perfect cylinders under axial compression, external pressure, and combinations of axial compression and internal or external pressure. Important results are obtained by taking into account prebuckling deformations and stresses induced by edge support. For example, the presence of these deformations and stresses can reduce the axial-compression buckling load of an unpressurized perfect cylinder to 50 percent of the classical value.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-190
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-27
    Description: An investigation was undertaken to determine the feasibility of depositing integrally bonded plasma-sprayed tungsten coatings onto 80-volume-percent tungsten - 20-volume-percent uranium dioxide composites. These composites were face clad with thin tungsten foil to inhibit uranium dioxide loss at elevated temperatures, but loss at the unclad edges was still significant. By preheating the composite substrates to approximately 3700 degrees F in a nitrogen environment, metallurgically bonded tungsten coatings could be obtained directly by plasma spraying. Furthermore, even though these coatings were thin and somewhat porous, they greatly inhibited the loss of uranium dioxide. For example, a specimen that was face clad but had no edge cladding lost 5.8 percent uranium dioxide after 2 hours at 4750 dgrees F in flowing hydrogen. A similar specimen with plasma-spray-coated edges, however, lost only 0.75 percent uranium dioxide under the same testing conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-1028 , GRC-E-DAA-TN44076
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  • 3
    Publication Date: 2019-08-14
    Description: Exploratory tests were made to determine the reduction of heat transfer resulting from ejection of gases at the stagnation point on a hemisphere-cone at a nominal Mach number of about 9 and at stagnation enthalpies up to 1600 BTU per pound. Helium, nitrogen, and argon gases were used as coolants. The ratio of mass flow of coolant to the mass flow of air swept out by the model projected area was less than 0.20 in all cases. The experimental heat-transfer data were normalized by the calculated stagnation-point values based on test conditions in the tunnel and are presented as a function of the surface distance from the stagnation point. The variation of shock standoff distances with mass flow and volumetric flow of the gaseous ejectants is presented along with photographs of the luminous flow field of the model during tests.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-983
    Format: application/pdf
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  • 4
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    In:  CASI
    Publication Date: 2019-08-14
    Description: The papers presented in this report represent the classified portion of the Second Manned Space Flight Meeting which was held in Dallas, TX, on April 22-24, 1963. The meeting was co-sponsored by the American Institute of Aeronautics and Astronautics and the National Aeronautics and Space Administration. The following subjects are discussed in the report: Manned Space Flight Programs, Launch Vehicles, Spacecraft Design, and Guidance and Control.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-861 , S-40
    Format: application/pdf
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