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  • Seismology  (9)
  • FLUID MECHANICS AND HEAT TRANSFER  (8)
  • Fluid Mechanics and Thermodynamics  (4)
  • 42.75
  • 1950-1954  (21)
  • 1953  (21)
  • 1
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    Progress report, Seismological Laboratory, California Institute of Technology, 1952 (1953)
    In:  Trans. Am. Geophys. Union, Beijing, Pergamon, vol. 34, no. 3-4, pp. 785-791, pp. 1246
    Details
    Publication Date: 1953
    Keywords: Seismology ; Project report/description ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    Larger shocks of 1951 (1953)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1951, no. 6, pp. 95, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Wave velocities at depths between 50 and 600 kilometers (1953)
    In:  Bull. Seism. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 43, no. 6, pp. 223-232, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Velocity analysis ; Seismology ; Earth model, also for more shallow analyses ! ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    Results from teleseismic records of the 1952 Kern County California, shocks (1953)
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Seismology ; Seismometer ; Teleseismic events ; Earthquake
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    BIBLIOGRAPHY SEISMOLOGY
  • 5
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    Larger shocks of 1952 (1953)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 1952, no. 6, pp. 104, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 6
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    Microseisms, microbaroms, storms and waves in western North America (1953)
    In:  Trans., Am. Geophys. Union, Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 34, no. 6, pp. 161-173, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Micro seismicity ; Waves ; Seismology ; Meteorology ; NOISE ; EOS
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    BIBLIOGRAPHY SEISMOLOGY
  • 7
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    Some general features of low-velocity layers (1953)
    In:  Bull. Geol. Soc. Am., Los Angeles California, 1 p., California Institute of Technology Pasadena, vol. 64, no. 6, pp. 1525, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1953
    Keywords: Low velocity layer ; Velocity analysis ; Seismology
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    BIBLIOGRAPHY SEISMOLOGY
  • 8
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    Geophysical and geological observations in the Pacific area and tectonic hypotheses (1953)
    Pacific Science Association
    In:  7th Congress Proceedings New Zealand (1949), vol. 2, Wellington, Pacific Science Association, vol. 10, no. GL-TR-89-0230, pp. 7-9, (ISBN 3-933346-037)
    Details
    Publication Date: 1953
    Keywords: Tectonics ; Seismology ; Geol. aspects
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Travel times of longitudinal waves from surface foci (1953)
    Nat. Acad. Sci.
    In:  Proceedings, vol. 39, Washington, Nat. Acad. Sci., vol. 10, no. GL-TR-89-0230, pp. 849-853, (ISBN 3-933346-037)
    Details
    Publication Date: 1953
    Keywords: Travel time ; Seismology ; P-waves
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    The Condensation Line of Air and the Heats of Vaporization of Oxygen and Nitrogen (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The condensation pressure of air was determined over the range of temperature from 60 to 85 K. The experimental results were slightly higher than the calculated values based on the ideal solution law. Heat of vaporization of oxygen was determined at four temperatures ranging from about 68 to 91 K and of nitrogen similarly at four temperatures ranging from 62 to 78 K.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TN-2969
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  • 11
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    An Analytical Study of Heat Requirements for Icing Protection of Radomes (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The heat requirements for the icing protection of two radome configurations have been studied over a range of design icing conditions. Both the protection limits of a typical thermal protection system and the relative effects of the various icing variables have been determined. For full evaporation of all impinging water, an effective heat density of 14 watts per square inch was required. When a combination of the evaporation and running wet surface systems was employed, a heat requirement of 5 watts per square inch provided protection at severe icing and operating conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-E53A22
    Format: application/pdf
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  • 12
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    Analogy Between Mass and Heat Transfer with Turbulent Flow (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analysis of combined heat and mass transfer from a flat plate has been made in terms of Prandtl t s simplified physical concept of the turbulent boundary layer. The results of the analysis show that for conditions of reasonably small heat and mass transfer, the ratio of the mass-and heat-transfer coefficients is dependent on the Reynolds number of the boundary layer, the Prandtl number of the medium of diffusion, and the Schmidt number of the diffusing fluid in the medium of diffusion. For the particular case of water evaporating into air, the ratio of mass-transfer coefficient to heat-transfer coefficient is found to be slightly greater than unity.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-3045
    Format: application/pdf
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  • 13
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    Impingement of Water Droplets on a Cylinder in an Incompressible Flow Field and Evaluation of Rotating Multicylinder Method for Measurement of Droplet-Size Distribution, Volume-Median Droplet-Size, and Liquid-Water Content in Clouds (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2904
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  • 14
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    Impingement of cloud droplets on aerodynamic bodies as affected by compressibility of air flow around the body (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2903
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  • 15
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    Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 40 The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures.. In general, the results showed that rotation will increase the convective heat transfer from a spinner, especially in the turbulent-flow regions. Rotation of the spinner at 1200 rpm and at a free-stream velocity of 275 miles per hour increased the Nusselt number parameter in the turbulent-flow region by 32 percent over that obtained with a stationary spinner; whereas in the nose region, where the flow was laminar, an increase of only 18 percent was observed. Transition from laminar to turbulent flow occurred over a large range of Reynolds numbers primarily because of surface roughness of the spinner. Operation at an angle of attack of 40 had only small effects on the local convective heat transfer for the model studied.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-RM-E53F02
    Format: application/pdf
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  • 16
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    A Method for Rapid Determination of the Icing Limit of a Body in Terms of the Stream Conditions (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of existing frictional heating were analyzed to determine the conditions under which ice formations on aircraft surfaces can be prevented. A method is presented for rapidly determining by means of charts the combination of-Mach number, altitude, and stream temperature which will maintain an ice-free surface in an icing cloud. The method can be applied to both subsonic and supersonic flow. The charts presented are for Mach numbers up to 1.8 and pressure altitudes from sea level to 45,000 feet.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2914
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  • 17
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    A Method for Determining Cloud-Droplet Impingement on Swept Wings (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The general effect of wing sweep on cloud-droplet trajectories about swept wings of high aspect ratio moving at subsonic speeds is discussed. A method of computing droplet trajectories about yawed cylinders and swept wings is presented, and illustrative droplet trajectories are computed. A method of extending two-dimensional calculations of droplet impingement on nonswept wings to swept wings is presented. It is shown that the extent of impingement of cloud droplets on an airfoil surface, the total rate of collection of water, and the local rate of impingement per unit area of airfoil surface can be found for a swept wing from two-dimensional data for a nonswept wing. The impingement on a swept wing is obtained from impingement data for a nonswept airfoil section which is the same as the section in the normal plane of the swept wing by calculating all dimensionless parameters with respect to flow conditions in the normal plane of the swept wing.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2931
    Format: application/pdf
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  • 18
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    Impingement of Droplets in 90 deg Elbows with Potential Flow (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Trajectories were determined for droplets in air flowing through 90 deg elbows especially designed for two-dimensional potential motion with low pressure losses. The elbows were established by selecting as walls of each elbow two streamlines of the flow field produced by a complex potential function that establishes a two-dimensional flow around a 90 deg bend. An unlimited number of elbows with slightly different shapes can be established by selecting different pairs of streamlines as walls. The elbows produced by the complex potential function selected are suitable for use in aircraft air-intake ducts. The droplet impingement data derived from the trajectories are presented along with equations in such a manner that the collection efficiency, the area, the rate, and the distribution of droplet impingement can be determined for any elbow defined by any pair of streamlines within a portion of the flow field established by the complex potential function. Coordinates for some typical streamlines of the flow field and velocity components for several points along these streamlines are presented in tabular form.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-2999
    Format: application/pdf
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  • 19
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    Impingement of Water Droplets on NACA 65A004 Airfoil and Effect of Change in Airfoil Thickness from 12 to 4 Percent at 4 deg Angle of Attack (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The trajectories of droplets in the air flowing past an NACA 65A004 a irfoil at an angle of attack of 4 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. The effect of a change in airfoil thickness from 12 to 4 percent at 4 deg angle of attack is presented by comparing the impingement calculations for the NACA 65A004 airfoil with those for the NACA 65(sub 1)-208 and 65(sub 1)-212 airfoils. The rearward limit of impingement on the upper surface decreases as the airfoil thickness decreases. The rearward limit of impingement on the lower surface increases with a decrease in airfoil t hickness. The total water intercepted decreases as the airfoil thickness is decreased.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-3047
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  • 20
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    Impingement of water droplets on NACA 65(1)-208 and 65(1)-212 airfoils at 4 degrees angle of attack (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The trajectories of droplets in the air flowing past NACA 65(1)-208 airfoil and an NACA 65(1)-212 airfoil, both at an angle of attack of 4 degrees, were determined. The amount of water in droplet form impinging on the airfoils, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface affected were calculated from the trajectories and are presented. The amount, extent, and rate of impingement of the NACA 65(1)-208 airfoil are compared with the results for the NACA 65(1)1-212 airfoil. Under similar conditions of operation, the NACA 65(1)-208 airfoil collects less water than the NACA 65(1)-212 airfoil. The extent of impingement on the upper surface of the NACA 65(1)-208 airfoil is much less than on the upper surface of the NACA 65(1)-212 airfoil, but on the lower surface the extents of impingement are about the same.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TN-2952
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  • 21
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    Notes on the Prediction of Shock-induced Boundary-layer Separation (1953)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The present status of available information relative to the prediction of shock-induced boundary-layer separation is discussed. Experimental results showing the effects of Reynolds number and Mach number on the separation of both laminar and turbulent boundary layer are given and compared with available methods for predicting separation. The flow phenomena associated with separation caused by forward-facing steps, wedges, and incident shock waves are discussed. Applications of the flat-plate data to problems of separation on spoilers, diffusers, and scoop inlets are indicated for turbulent boundary layers.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-L53I16a
    Format: application/pdf
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