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  • Fluid Mechanics and Thermodynamics
  • 1975-1979  (11)
  • 1970-1974  (4)
  • 1950-1954  (30)
  • 1935-1939  (3)
Collection
Keywords
Years
Year
  • 1
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    CSM/LM Spacecraft Operational Data Book. Volume 3: Mass Properties Data Book (1971)
    In:  CASI
    Details
    Publication Date: 2019-11-09
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-69016 , SNA-8-D-027-VOL-3-REV-3 , JSC-E-DAA-TN75190
    Format: application/pdf
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  • 2
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    Fluid valve with wide temperature range (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A fluid valve suitable for either metering or pressure regulating fluids at various temperatures is provided for a fuel system as may be utilized in an aircraft gas turbine engine. The valve includes a ceramic or carbon pad which cooperates with a window in a valve plate to provide a variable area orifice which remains operational during large and sometimes rapid variations in temperature incurred from the use of different fuels.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 3
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    The Effect of Streamlining the Afterbody of an N.A.C.A. Cowling (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The drag and the power cost associated with the changing of the nose of a nacelle from a streamline shape to a conventional N.A.C.A. cowling shape was investigated in the N.A.C.A. 20-foot tunnel. Full-scale propellers and nacelles were used. The increment of drag associated with the change of nose shapes was found to be critically dependent on the afterbody of the nacelle. Two streamline afterbodies were tested. The results fo the tests with the more streamlined afterbody showed that the added drag due to the open-nose cowling was only one-fourth of the drag increase obtained with the other afterbody. The results of this research indicate that the power cost, in excess of that with a streamline nose, of using an N.A.C.A. cowling in front of a well-designed afterbody to enclose a 1,500-horsepower engine in an airplane with a speed of 300 miles per hour amounts to 1.5 percent of the engine power. If the open-nose cowling is credited with 1 percent because it cools the front of the cylinders, the non-useful power cost amounts to only 0.5 percent of the engine power.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-SR-136
    Format: application/pdf
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  • 4
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    Boundary Layer Effect on the Surface Pressure of an Infinite Cone in Supersonic Flow (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The theory of Taylor and Maccoll (Ref,1) gives the surface pressure on an infinite cone in supersonic flow as a function of the cone vertex angle and the free stream Mach number and static pressure for a gas of vanishing viscosity. When a slender conical probe is used together with an impact pressure probe to determine the static pressure and Mach number in a low density gas stream, it is desirable to have some theoretical estimate of the effect of viscous boundary layer on the probe readings. Theoretical and experimental results with respect to impact probes have been presented in Refs. 5 and 6. A simple approximation for a conical probe based on linearized supersonic flow and compressible boundary layer theory is presented here.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: HE-150-80
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  • 5
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    Aseptic fluid transfer system (1977)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A method and means is provided, which permits the transfer of fluids between separate detached containers, in a manner which preserves the sterility of the fluids during and after their transfer.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 6
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    Reclaiming Waste Heat (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: 'Air-O-Space' heater, based on spacecraft heat, requires no fuel other than electricity to run fan. Installed in chimney flue, heat pipes transfer heat from waste hot gases (but not the gases themselves) to fresh air blown across the other end of the pipes. It can transport roughly 500 times the heat flux of the best solid conductors with a temperature drop of less than 3 degrees per foot. This instrument has also been used by Kin-Tek Laboratories Inc. to produce an instrument to calibrate gas analyzers for air-pollution monitoring.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Spinoff 1976; 75
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  • 7
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    Fuel cell heat and mass plate (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A novel method and apparatus is provided for controlling heat and mass inventory in a fuel cell. Heat and mass, e.g. water, generated in the cell are removed by heat transfer and capillary action.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 8
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    Variable Conductance Heat Pipe Technology (1974)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A research and development program in variable conductance heat pipe technology is reported. The project involved: (1) theoretical and/or experimental studies in hydrostatics, (2) hydrodynamics, (3) heat transfer into and out of the pipe, (4) fluid selection, and (5) materials compatibility. The development, fabrication, and test of the space hardware resulted in a successful flight of the heat pipe experiment on the OAO-3 satellite. A summary of the program is provided and a guide to the location of publications on the project is included.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-CR-114750 , TRW-13111-6060-RU-00
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  • 9
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    Analysis of Free-Flight Laminar, Transitional, and Turbulent Heat-Transfer Results at Free-Stream Mach Numbers Near 20 (Reentry F) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Laminar, transitional, and turbulent heat-transfer data were measured during a reentry flight at a Mach number of 20 on a 5 deg half-angle cone 3.962 m (13 ft) long with an initial nose tip radius of 0.254 cm (0.1 in.). The free-stream Reynolds number increased during the prime data period from 7.0 x 10(exp 6) to 51.5 x 10(exp 6) per meter (2.1 x 10(exp 6) to 15.7 x 10(exp 6) per foot) and the ratio of wall to total temperature varied from 0.053 to 0.12. The angle of attack was less than 1deg for the prime data period. The experimental laminar and turbulent heating rates are compared with results from existing flat-plate prediction methods. At conditions of minimal tip blunting and angle of attack (above 26.8 km (88 000 ft)), values from a flat-plate laminar method agreed within 20 percent with the laminar data. The Schultz-Grunow skin-friction equation with reference enthalpy; conditions, with the Reynolds number based on distance from the transition location, and with the Colburn Reynolds analogy agreed within 10 percent with the experimental turbuleiit heating data. The Van Driest n skin-friction equation with Reynolds number greater than 10(exp 7) based on distance from the peak heating point and the Colburn Reynolds analogy was also within approximately 10 percent of the experimental turbulent heating data. A data correlation jbf the extent of transition and a simple empirical transition-zone heating correlation were also presented.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-2335 , L-7803
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  • 10
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    Thermal Analysis Methods and Basic Heat-Transfer Data for a Turbulent Heating Flight Experiment at Mach 20 (Reentry F) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A heat-transfer experiment was flight conducted on a 5 deg half-angle cone, 396.2 cm (13 ft) in length, as it entered the sensible atmosphere under laminar, transitional, and turbulent boundary-layer conditions at a free-stream Mach number of about 20. Accurate turbulent-heat-transfer data with natural transition were obtained for correlation with theories in regions of simultaneous high Mach number, Reynolds number, enthalpy, and total-to-wall temperature ratio. Temperatures were measured at four depths through the 15.24-mm-thick (0.600-in.) beryllium wall. Experimental heating rates at 20 stations on the cone were determined independently from the outermost temperature measurement and from the temperature measurement at the second depth by a single-thermocouple inverse method and also from the temperature histories at all four depths by an integral method. The thermal data analysis procedure, associated problems, and results are presented herein.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-2282 , L-7520
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