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  • FLUID MECHANICS AND HEAT TRANSFER
  • 2025-2025
  • 2010-2014
  • 1970-1974  (3)
  • 1965-1969  (2)
  • 1950-1954  (3)
  • 1987
  • 1986
  • 1973  (2)
  • 1970  (1)
  • 1967  (2)
  • 1951  (3)
Collection
Keywords
Years
  • 2025-2025
  • 2010-2014
  • 1970-1974  (3)
  • 1965-1969  (2)
  • 1950-1954  (3)
    • +
Year
  • 1
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    Heat pipe with dual working fluids (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A heat pipe design is offered that utilizes an auxiliary working fluid. The fluid, although being less efficient than the main working fluid, remains liquid at low heat loads when the main working fluid freezes.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Heat pipe development (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The objective of this program was to investigate analytically and experimentally the performance of heat pipes with composite wicks--specifically, those having pedestal arteries and screwthread circumferential grooves. An analytical model was developed to describe the effects of screwthreads and screen secondary wicks on the transport capability of the artery. The model describes the hydrodynamics of the circumferential flow in triangular grooves with azimuthally varying capillary menisci and liquid cross-sections. Normalized results were obtained which give the influence of evaporator heat flux on the axial heat transport capability of the arterial wick. In order to evaluate the priming behavior of composite wicks under actual load conditions, an 'inverted' glass heat pipe was designed and constructed. The results obtained from the analysis and from the tests with the glass heat pipe were applied to the OAO-C Level 5 heat pipe, and an improved correlation between predicted and measured evaporator and transport performance were obtained.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-156669 , DTM-73-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Multi-chamber controllable heat pipe (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A temperature controllable heat pipe switching device is reported. It includes separate evaporating and condensing chambers interconnected by separate vapor flow and liquid return conduits. The vapor flow conduit can be opened or closed to the flow of vapor, whereas the liquid return conduit blocks vapor flow at all times. When the vapor flow path is open, the device has high thermal conductivity, and when the vapor flow path is blocked the device has low thermal conductivity.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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    NASA TECHNICAL REPORTS
  • 4
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    Heat pipe application for spacecraft thermal control (1967)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-163017 , SDO-2039
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Mechanics of Boundary Layer Transition. Part 5: Boundary Layer Stability theory in incompressible and compressible flow (1967)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The fundamentals of stability theory, its chief results, and the physical mechanisms at work are presented. The stability theory of the laminar boundary determines whether a small disturbance introduced into the boundary layer will amplify or damp. If the disturbance damps, the boundary layer remains laminar. If the disturbance amplifies, and by a sufficient amount, then transition to turbulence eventually takes place. The stability theory establishes those states of the boundary layer which are most likely to lead to transition, identifys those frequencies which are the most dangerous, and indicates how the external parameters can best be changed to avoid transition.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-162112 , VKI-LECTURE-SERIES-3-PT-5 , Jan 15, 1968 - Jan 19, 1968; Rhodes-Saint-Genese; Belgium
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    NASA TECHNICAL REPORTS
  • 6
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    Comparison of Heat Transfer from Airfoil in Natural and Simulated Icing Conditions (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation of the heat transfer from an airfoil in clear air and in simulated icing conditions was conducted in the NACA Lewis 6- by 9-foot icing-research tunnel in order to determine the validity of heat-transfer data as obtained in the tunnel. This investiation was made on the same model NACA 65,2-016 airfoil section used in a previous flight study, under similar heating, icing, and operating conditions. The effect of tunnel turbulence, in clear air and in icingwas indicated by the forward movement of transition from laminar to turbulent heat transfer. An analysis of the flight results showed the convective heat transfer in icing to be considerably different from that measured in clear air and. only slightly different from that obtained in the icing-research tunnel during simulated icing.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2480
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A General Correlation of Temperature Profiles Downstream of a Heated-Air Jet Directed Perpendicularly to an Air Stream (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the temperature profile downstream of a heated-air jet directed perpendicularly to an air stream. The profiles were determined at several positions downstream of the jet as functions of jet density, jet velocity, freestream density, free-stream velocity, jet temperature, and orifice flow coefficient. A method is presented which yields a good approximation of the temperature profile in terms of dimensionless parameters of the flow and geometric conditions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2466
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    An Empirical Method Permitting Rapid Determination of the Area, Rate and Distribution of Water-Drop Impingement on an Airfoil of Arbitrary Section at Subsonic Speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An empirical method for the determination of the area, rate, and distribution of water-drop impingement on airfoils of arbitrary section is presented. The procedure represents an initial step toward the development of a method which is generally applicable in the design of thermal ice-prevention equipment for airplane wing and tail surfaces. Results given by the proposed empirical method are expected to be sufficiently accurate for the purpose of heated-wing design, and can be obtained from a few numerical computations once the velocity distribution over the airfoil has been determined. The empirical method presented for incompressible flow is based on results of extensive water-drop. trajectory computations for five airfoil cases which consisted of 15-percent-thick airfoils encompassing a moderate lift-coefficient range. The differential equations pertaining to the paths of the drops were solved by a differential analyzer. The method developed for incompressible flow is extended to the calculation of area and rate of impingement on straight wings in subsonic compressible flow to indicate the probable effects of compressibility for airfoils at low subsonic Mach numbers.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2476
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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