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  • Other Sources  (263)
  • Aircraft Propulsion and Power
  • Cell & Developmental Biology
  • Fisheries
  • Fluid Mechanics and Thermodynamics
  • Inorganic Chemistry
  • Limnology
  • Seismicity
  • 1960-1964  (72)
  • 1945-1949  (191)
Collection
Source
Keywords
Publisher
Years
Year
  • 1
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    Die Seismizität der Türkei (1964)
    In:  Pageoph, Charleston, South Carolina, California Division of Mines San Francisco, vol. 57, no. 7, pp. 103-116, pp. L23602, (ISSN: 1340-4202)
    Details
    Publication Date: 1964
    Keywords: Seismicity ; Turkey ; NAF ; Fault zone ; EAF ; PAG ; Oecal ; Ocal
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    BIBLIOGRAPHY SEISMOLOGY
  • 2
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    The seismicity of East Africa, the Gulf of Aden and the Arabian and Red Seas (1964)
    In:  Bull. Seism. Soc. Am., Washington, D.C., AGU, vol. 54, no. 3, pp. 1927-1940, pp. 2090, (ISSN: 1340-4202)
    Details
    Publication Date: 1964
    Keywords: Seismicity ; BSSA
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    BIBLIOGRAPHY SEISMOLOGY
  • 3
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    Seismicity of Europe (1964)
    European Seismological Commission
    In:  Progress report 4, I.A.S.P.E.I., Washington, D.C., European Seismological Commission, vol. C 560, 183 pp., no. 57, pp. 451-457, (ISBN 3-933346-037)
    Details
    Publication Date: 1964
    Keywords: Tectonics ; Plate tectonics ; Statistical investigations ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 4
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    The Influence of Prebuckling Deformations and Stresses on the Buckling of Perfect Cylinders (1964)
    In:  CASI
    Details
    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
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  • 5
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    Fuel Retention Improvement at High Temperatures in Tungsten-Uranium Dioxide Dispersion Fuel Elements by Plasma-Spray Cladding (1964)
    In:  CASI
    Details
    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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  • 6
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    Experimental Data on Stagnation-Point Gas Injection Cooling on a Hemisphere-Cone in a Hypersonic Arc Tunnel (1964)
    In:  CASI
    Details
    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
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  • 7
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    Proceedings of the Second Manned Space Flight Meeting (1964)
    In:  CASI
    Details
    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
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  • 8
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    Strain release in the circum-pacific belt, Chile: 1960 (1963)
    In:  J. Geophys. Res., Hoboken, NJ, 633 pp. + CD-ROM, Pergamon, vol. 68, no. 19, pp. 5531-5544, pp. B05309, (ISBN 0-471-26610-8)
    Details
    Publication Date: 1963
    Keywords: Strain ; Earthquake ; Seismicity ; JGR
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    BIBLIOGRAPHY SEISMOLOGY
  • 9
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    Über das Problem der Aseismizität der Antarktis und Grönlands (1963)
    In:  Problemi Arktiki i Antarktiki, Darmstadt, Wissenschaftliche Buchgesellschaft, vol. 12, no. 3, pp. 197-206, pp. B06304, (ISSN: 1340-4202)
    Details
    Publication Date: 1963
    Keywords: Seismicity ; Stress ; Antarctica
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    BIBLIOGRAPHY SEISMOLOGY
  • 10
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    Computer studies of microseism statistics with application to prediction and detection (1963)
    MIT
    In:  Ph.D. Thesis, Houston, 19 pp., April 1989, MIT, vol. 10, no. EL-1021R, pp. 235-239, (ISBN 3-933346-037)
    Details
    Publication Date: 1963
    Keywords: NOISE ; Detectors ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 11
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    Radiant Heat Transfer to Absorbing Gases Enclosed Between Parallel Flat Plates with Flow and Conduction (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An analysis is presented for obtaining two-dimensional temperature profiles and heat transfer in a radiation-absorbing gray gas of uniform absorptivity under the combined influence of thermal radiation, conduction, and gas flow. The gas is enclosed in a channel of infinite width and finite length formed by two semi-infinite parallel flat plates. These plates are black emitting surfaces, and the ends of the channel are formed by porous black surfaces through which the gas can flow into or out of the channel. These porous black end surfaces are used to simulate the radiation environment external to the channel. First, results are obtained for heat transfer between the plates in the absence of both conduction and flow. These results are found to be in good agreement with those obtained for the same conditions by previous workers. Results are then presented for heat transfer between the plates for the case of a radiating and conducting, but stagnant, gas separating the plates. The effects of the interactions between radiation and conduction are discussed. It was found that the heat transfer for combined radiation and conduction in an absorbing gas is slightly greater than the sum for each process taken separately. Finally, results are given for heat transfer from the plates to a flowing, radiating gas in the absence of conduction. The two plates are at the same temperature, and the gas enters the channel with uniform velocity and temperature. The results obtained for this case indicate that the heat transferred to the flowing gas from the constant temperature surfaces goes through a maximum as the absorptivity of the gas increases. This is in qualitative agreement with earlier results obtained by other investigators. All the results are presented in terms of dimensionless parameters, for the sake of generality, and the derivation of the dimensionless parameters, which are indicative of the effects of conduction and flow is presented.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-154
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  • 12
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    Measurement of Thermal Radiation Properties of Solids (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The overall objectives of the Symposium were to afford (1) an opportunity for workers in the field to describe the equipment and procedures currently in use for measuring thermal radiation properties of solids, (2) an opportunity for constructive criticism of the material presented, and (3) an open forum for discussion of mutual problems. It was also the hope of the sponsors that the published proceedings of the Symposium would serve as a valuable reference on measurement techniques for evaluating thermal radiation properties of solids, partic.ularly for those with limited experience in the field. Because of the strong dependence of emitted flux upon temperature, the program committee thought it advisable to devote the first session to a discussion of the problems of temperature measurement. All of the papers in Session I were presented at the request of and upon topics suggested by the Committee. Because of time and space limitations, it, was impossible to consider all temperature measurement problems that might arise--the objective was rather to call to the attention of the reader some of the problems that might be encountered, and to provide references that might provide solutions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-SP-31 , Symposium on Measurement of Thermal Radiation Properties of Solids; Sep 05, 1962 - Sep 07, 1962; Dayton, OH; United States
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  • 13
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    Study of the Effect of a Closed-End Side Branch on Sinusoidally Perturbed Flow of Liquid in a Line (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Classical undamped acoustic-wave theory was used to determine analytical relations among sinusoidal perturbations of pressure and flow at the ends of a hydraulic-transmission line having a closed-end branch of arbitrary length attached at an arbitrary point. Experimental data were obtained for the equilateral case (a branch half as long as the main line connected to the main line at the midpoint) at mean flow speeds of 5 to 10 feet per second. Measured pressure-perturbation ratios agreed closely with analytical predictions. As frequencies for which the branch length was an odd multiple of 1/4 wavelength, waves in the main line were almost completely reflected at the junction point.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-1876 , E-2036
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  • 14
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    Propulsion and Power Generation (1963)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-50121
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  • 15
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    Estimated Viscosities and Thermal Conductivities of Gases at High Temperatures (1962)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Viscosities and thermal conductivities, suitable for heat-transfer calculations, were estimated for about 200 gases in the ground state from 100 to 5000 K and 1-atmosphere pressure. Free radicals were included, but excited states and ions were not. Calculations for the transport coefficients were based upon the Lennard-Jones (12-6) potential for all gases. This potential was selected because: (1) It is one of the most realistic models available and (2) intermolecular force constants can be estimated from physical properties or by other techniques when experimental data are not available; such methods for estimating force constants are not as readily available for other potentials. When experimental viscosity data were available, they were used to obtain the force constants; otherwise the constants were estimated. These constants were then used to calculate both the viscosities and thermal conductivities tabulated in this report. For thermal conductivities of polyatomic gases an Eucken-type correction was made to correct for exchange between internal and translational energies. Though this correction may be rather poor at low temperatures, it becomes more satisfactory with increasing temperature. It was not possible to obtain force constants from experimental thermal conductivity data except for the inert atoms, because most conductivity data are available at low temperatures only (200 to 400 K), the temperature range where the Eucken correction is probably most in error. However, if the same set of force constants is used for both viscosity and thermal conductivity, there is a large degree of cancellation of error when these properties are used in heat-transfer equations such as the Dittus-Boelter equation. It is therefore concluded that the properties tabulated in this report are suitable for heat-transfer calculations of gaseous systems.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-132
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  • 16
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    Measurement of Local Heat Transfer Coefficients for Flow of Hydrogen and Helium in a Smooth Tube at High Surface to Fluid Bulk Temperature Ratios (1962)
    In:  CASI
    Details
    Publication Date: 2019-06-26
    Description: Local values of heat transfer coefficients have been measured experimentally for helium and hydrogen gas flowing through an electrically heated inconel tube. The experiment was conducted primarily to determine the effect on the heat transfer coefficient of a large density change, radially, in the heat transfer fluid. This large density change was accomplished with relatively high surface temperatures as compared to fluid bulk temperatures or more commonly referred to as high surface to fluid bulk temperature ratio. The large temperature ratio was achieved by precooling the gas with liquid nitrogen. Data were measured for local values of surface to fluid bulk temperature ratios up to 4.5, Reynolds numbers in the turbulent flow region, surface temperatures up to 2300 R, heat flux up to 1,600,000 Btu/(hr)(sq ft) and length to diameter ratio of 250. A comparison of this data with the conventional heat transfer correlation equation (Dittus-Boelter eq.) is shown on a curve of Nusselt number divided by Prandtl number versus the Reynolds number. The gas properties were evaluated at the film temperature and the Reynolds number was modified by evaluating the velocity term at the fluid bulk temperature and the density at the film temperature.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: E-1721 , GRC-E-DAA-TN67415
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  • 17
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    Analysis of Thermal-Protection Systems for Space-Vehicle Cryogenic-Propellant Tanks (1962)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: Analytical techniques are presented that permit the calculation of heat-transfer rates with various thermal-protection systems for liquid-cryogenic-propellant tanks subjected to on-board, solar, and planetary heat fluxes . The effectiveness of these protection systems in reducing propellant heating is shown both for ideal heat-transfer models and for a simplified hydrogen-oxygen terminal stage used for typical Mars missions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-130 , E-488
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  • 18
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    A Preliminary Theoretical Study of the Expansion Tube, a New Device for Producing High-Enthalpy Short-Duration Hypersonic Gas Flows (1962)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The device considered utilizes an unsteady expansion process for the purpose of total-enthalpy multiplication. Analyses were conducted for both perfect and real air in equilibrium, assuming idealized diaphragm bursts, centered expansion waves, and continuum flow. Results of the study showed the expansion tube capable of outperforming the conventional shock tunnel by a factor of approximately 2 in velocity for the same test-section ambient density and pressure. The degree of dissociation is low at all phases of the thermodynamic cycle in the expansion tube; thus the test-section air has a good possibility of being in equilibrium. Maximum pressures involved in the cycle for duplicating a typical reentry from a lunar mission are low enough for existing pressure-vessel techniques. Both the known and anticipated advantages and disadvantages of this new concept are also discussed.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-133
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  • 19
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    A Preliminary Theoretical Study of the Expansion Tube, a New Device for Producing High-Enthalpy Short-Duration Hypersonic Gas Flows (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A preliminary theoretical study was conducted of a new technique for producing high-enthalpy gas flows. The device considered utilizes an unsteady expansion process for the purpose of total-enthalpy multiplication. Analyses were conducted for both perfect and real air in equilibrium, assuming idealized diaphragm bursts, centered expansion waves, and continuum flow. Results of the study showed the expansion tube capable of outperforming the conventional shock tunnel by a factor of approximately 2 in velocity for the same test-section ambient density and pressure. The degree of dissociation is low at all phases of the thermodynamic cycle in the expansion tube; thus the test-section air has a good possibility of being in equilibrium. Maximum pressures involved in the cycle for duplicating a typical reentry from, a lunar mission are low enough for existing pressure-vessel techniques. Both the known and anticipated advantages and disadvantages of this new concept are also discussed.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-133
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  • 20
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    Combined Radiation and Forced Convection for Flow of a Transparent Gas in a Tube with Sinusoidal Axial Wall Heat Flux Distribution (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An analysis is made of the influence that radiation exchanges between elements on the inside surface of a tube have on the wall and gas temperature distributions for forced-convection flow. The wall heat generation has a chopped sine distribution with length along the tube, which is a distribution often encountered in nuclear-reactor channels. The flowing gas is assumed transparent to thermal radiation and hence does not participate directly in the radiative exchange process. Axial heat conduction is neglected in the gas and tube wall, and the convective-heat-transfer coefficient and fluid properties are assumed constant. Several numerical examples are given to illustrate the effects of eight independent parameters such as wall emissivity, Stanton number, and length-diameter ratio. In some instances the radiation exchanges reduced the peak wall temperature or caused a reduction in the exit gas temperature because of radiation losses from the tube end openings.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-1441 , E-1672
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  • 21
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    Observations on Cavitation Damage in a Flowing System (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Cavitation damage to specimens of stainless steel, carbon steel, aluminum, and plexiglas, placed in a cavitating venturi using water and mercury as test fluids is mostly in the form of irregularly shaped pits which do not change with additional exposure to the cavitating field within the limited durations utilized. The rate of damage is very high initially, decreases for a relatively short period of time, then increases again up to the maximum test durations of 150 hours with water and 270 hours with mercury. Observation of damage effects by several independent techniques, using a variety of specimen materials, with two different fluids under various fluid dynamic conditions, leads to a suggested correlating model in terms of the cavitation bubble density and energy and specimen material strength.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: ORA Tech. Report 03424-4-T
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  • 22
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    Investigation of the Damping of Liquids in Right-Circular Cylindrical Tanks, Including the Effects of a Time-Variant Liquid Depth (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An experimental investigation was conducted to determine the effects of several basic variables upon the damping of the fundamental antisymmetric mode of liquids in right-circular cylindrical tanks without baffles. The variables examined include liquid depth, efflux rate, liquid amplitude, kinematic viscosity, and tank size. The data are presented in dimensionless form and compared with available theory. For the range of variables examined, variations of efflux rate and liquid amplitude were found to have no significant effects on the liquid damping. The following theoretical relationship was found to be adequate for the prediction of the variation of damping with liquid depth, kinematic viscosity, and tank size: [for equation see full text] where v is the kinematic viscosity, R is the cylinder radius, g is the acceleration due to gravity, and h is the liquid depth. However, the constant K was experimentally found in this investigation to have the value 5.23, which is 50 percent higher than the theoretically predicted value.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-1367
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  • 23
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    Absorption and Emission Characteristics of Diffuse Spherical Enclosures (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: An analysis was made to determine the energy absorbed when radiation from an external source enters a spherical cavity with diffusely reflecting walls. It was found that both the overall energy absorbed in the cavity and the local distribution of absorbed energy could be expressed in terms of simple algebraic equations that are valid for any arbitrary spatial and directional distribution of the incoming radiation. In addition, the characteristics of an isothermal spherical cavity as a possible source of near black-body radiation were investigated. This information was also expressed by simple algebraic relations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-1289 , E-1622
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  • 24
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    On the Dynamic Characteristics of Free-Liquid Jets and a Partial Correlation with Orifice Geometry (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A technique for evaluating the dynamic characteristics of free-liquid jets on a comparative basis is presented. This method consists of determining the pressure distribution produced by the perpendicular impingement of a jet upon a flat plate and using these data for comparing and categorizing jets with unknown properties in terms of similar data produced by jets having known characteristics-i.e., with jets produced by fully developed turbulent flow, fully developed laminar flow, and a jet having a near-uniform velocity profile. The visual characteristics, as well as both the mean and the fluctuating pressure distributions, are presented for these three reference configurations and for a number of jets produced by orifices having varying length-diameter ratios, combined with varying degrees of surface roughness in the initial five diameters of straight bore.
    Keywords: Aircraft Propulsion and Power
    Type: JPL-TR-32-207
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  • 25
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    Proceedings of Nuclear Propulsion Conference (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-CR-136951 , TID-7653-BK-1-PT-2 , HQ-E-DAA-TN19851 , Nuclear Propulsion Conference; Aug 15, 1962 - Aug 17, 1962; Monterey, CA; United States
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  • 26
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    Experimental Observations of Aerodynamic and Heating Test on Insulating Heat Shields (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Several different types of insulating heat shields have been subjected to aerodynamic tests and radiant-heating tests in order to obtain a better insight into the problems involved when the primary structure of m aerodynamically heated vehicle is substantially cooler than the exposed external surface. One of the main problems was considered to be a proper allowance for thermal expansion caused by these large temperature differences, so that undue distortion or thermal stresses would not occur in either the outer shield or the underlying structure. corrugated outer skin with suitably designed expansion joints was a feature of all the specimens tested.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-1237
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  • 27
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    A note on the seismicity of the Ross Sea region (1961)
    In:  Geophys. J. R. astr. Soc., Oxford and Edinburgh, Blackwell Scientific Publications, vol. 5, no. 2, pp. 252-253, pp. L23301, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1961
    Keywords: Seismicity ; Seismology ; GJRaS
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    BIBLIOGRAPHY SEISMOLOGY
  • 28
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    A statistical study on the occurrence of aftershocks (1961)
    In:  Geophys. Mag., Luxembourg, Conseil de l'Europe, vol. 30, no. 1, pp. 521-605, pp. 1068, (ISSN: 1340-4202)
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    Publication Date: 1961
    Keywords: Statistical investigations ; Aftershocks ; Seismicity
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    BIBLIOGRAPHY SEISMOLOGY
  • 29
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    Earthquakes, distribution, magnitude, and field studies of (1961)
    Pergamon Press
    In:  Bull., Polar Proj. OP-O3A4, Encyclopaedic dictionary of physics 2, Oxford, Pergamon Press, vol. 2, no. XVI:, pp. 588-591, (ISBN: 3-540-23712-7)
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    Publication Date: 1961
    Keywords: Seismology ; Seismicity ; Magnitude
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    BIBLIOGRAPHY SEISMOLOGY
  • 30
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    Comparison of Temperatures of Flames on Porous Burners (1961)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Combustion and Flame; Volume 5; No. 1
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  • 31
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    An Experimental Study of Boiling in Reduced and Zero Gravity Fields (1961)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A pool boiling apparatus was mounted on a counterweighted platform which could be dropped a distance of nine feet. By varying the size of the counterweight, the effective gravity field on the equipment was adjusted between zero and unity. A study of boiling burnout in water indicated that a variation in the critical heat flux according to the one quarter power of gravity was reasonable. A consideration of the transient burnout process was necessary in order to properly interpret the data. A photographic study of nucleate boiling showed how the velocity of freely rising vapor bubbles decreased as gravity was reduced. The bubble diameters at the time of breakoff from the heated surface were found to vary inversely as gravity to the 1/3.5 power. Motion pictures were taken to illustrate both nucleate and film boiling in the low gravity range.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Journal of Heat Transfer; 243-253
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  • 32
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    Viscosity Difference Measurements for Normal and Para Liquid Hydrogen Mixtures (1961)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: The absence of experimental data in the literature concerning a viscosity difference for normal and equilibrium liquid hydrogen may be attributed to the limited reproducibility of "oscillating disk" measurements in a liquid-hydrogen environment. Indeed, there is disagreement over the viscosity values for equilibrium liquid hydrogen even without proton spin considerations. Measurements presented here represent the first application of the piezoelectric alpha quartz torsional oscillator technique to liquid-hydrogen viscosity measurements.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Physics of Fluids; Volume 4; No. 1; 159-160
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  • 33
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    Ballistic Range Measurements of Stagnation-Point Heat Transfer in Air and in Carbon Dioxide at Velocities up to 18,000 Feet Per Second (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A new technique for measuring heat-transfer rates on free-flight models in a ballistic range is described in this report. The accuracy of the heat-transfer rates measured in this way is shown to be comparable with the accuracy obtained in shock-tube measurements. The specific results of the present experiments consist of measurements of the stagnation-point heat-transfer rates experienced by a spherical-nosed model during flight through air and through carbon dioxide at velocities up to 18,000 feet per second. For flight through air these measured heat-transfer rates agree well with both the theoretically predicted rates and the rates measured in shock tubes. the heat-transfer rates agree well with the rates measured in a shock tube. Two methods of estimating the stagnation-point heat-transfer rates in carbon dioxide are compared with the experimental measurements. At each velocity the measured stagnation-point heat-transfer rate in carbon dioxide is about the same as the measured heat-transfer rate in air.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-777 , A-427
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  • 34
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    Sound Radiation from a Turbulent Boundary Layer (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: If the restriction of incompressibility in the turbulence problem is relaxed, the phenomenon of energy radiation in the form of sound from the turbulent zone arises. In order to calculate this radiated energy, it is shown that new statistical quantities, such as time-space correlation tensors, have to be known within the turbulent zone in addition to the conventional quantities. For the particular case of the turbulent boundary layer, indications are that the intensity of radiation becomes significant only in supersonic flows. Under these conditions, the recent work of Phillips is examined together with some experimental findings of the author. It is shown that the qualitative features of the radiation field (intensity, directionality) as predicted by the theory are consistent with the measurements; however, even for the highest Mach number flow, some of the assumptions of the asymptotic theory are not yet satisfied in the experiments. Finally, the question of turbulence damping due to radiation is discussed, with the result that in the Mach number range covered by the experiments, the energy lost from the boundary layer due to radiation is a small percentage of the work done by the wall shearing stresses.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: JPL-TR-32-119
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  • 35
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    Experimental Investigation of a High-Speed Hydrofoil with Parabolic Thickness Distribution and an Aspect Ratio of 3 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An experimental investigation has been made to determine the hydro-dynamic characteristics of a 10-percent-thick hydrofoil with an aspect ratio of 3 designed to operate with acceptable efficiency at speeds in the neighborhood of 100 knots (169 fps). A cambered hydrofoil model with parabolic thickness distribution was investigated at a depth of chord over a range of angles of attack from -0.5 deg to 4.0 deg and at speeds from 120 to 210 fps. substantially wider range of operation at acceptable lift-drag ratios as well as higher maximum lift-drag-ratio values than did a hydrofoil of similar design with an aspect ratio of 1.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-728 , L-1358
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  • 36
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    A Study of Laminar Compressible Viscous Pipe Flow Accelerated by an Axial Body Force, with Application to Magnetogasdynamics (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A study is made of the steady laminar flow of a compressible viscous fluid in a circular pipe when the fluid is accelerated by an axial body force. The application of the theory to the magnetofluidmechanics of an electrically conducting gas accelerated by electric and magnetic fields is discussed. Constant viscosity, thermal conductivity, and electrical conductivity are assumed. Fully developed flow velocity and temperature profiles are shown, and detailed results of the accelerating flow development, including velocity and pressure as functions of distance, are given for the case where the axial body force is constant and for the case where it is a linear function of velocity. From these results are determined the pipe entry length and the pressure difference required.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-855 , A-396
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  • 37
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    Loads Induced on a Flat-Plate Wing by an Air Jet Exhausting Perpendicularly through the Wing and Normal to a Free-Stream Flow of Mach Number 2.0 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Measurements were made of loads induced on a flat-plate wing by an air jet exhausting perpendicularly through the wing and normal to the free-stream flow.The investigation was conducted at a free-stream Mach number of 2.0 and a Reynolds number per foot of 14.4 x 10(exp 6). An axially symmetric sonic nozzle and two supersonic nozzles were employed for the jets. The supersonic nozzles consisted of an axially symmetric nozzle with exit Mach number of 3.44 and a two-dimensional nozzle with exit Mach number of 1.76. The ratio of nozzle total pressure to free-stream static pressure was varied from 20 to 110. Negative loads were induced on the flat-plate wing by all the jets. As the nozzle pressure ratio was increased the magnitude of interference loads due to jet thrust decreased. The chordwise center-of-pressure location generally moved toward the nozzle center line as the pressure ratio was increased.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-649 , L-1184
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  • 38
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    An Investigation of Transonic Flow Fields Surrounding Hot and Cold Sonic Jets (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation at free-stream Mach numbers of 0.90 t o 1.10 was made to determine (1) the jet boundaries and the flow fields around hot and cold jets, and (2) whether a cold-gas jet could adequately simulate the boundary and flow field of hot-gas jet. Schlieren photographs and static-pressure surveys were taken in the vacinity of a sonic jet which was operated over a range of jet pressure ratios of 1 to 6, specific heat ratios at the nozzle exit of 1.29 and 1.40, and jet temperatures up to 2600 R.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-853 , A-368
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  • 39
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    Absorption and Emission Characteristics of Diffuse Spherical Enclosures (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The thermal radiation characteristics of spherical cavities are of practical interest in connection with the absorption of radiant energy for both space-vehicle and terrestrial applications. Also, spherical cavities are of potential use as sources of black-body energy. The purpose of this brief paper is to determine both the absorption and emission characteristics of spherical cavities which are diffuse reflectors and emitters.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: HQ-E-DAA-TN59059
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  • 40
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    Exploratory Investigation of Transpiration Cooling of a 40 Degree Double Wedge Using Nitrogen and Helium as Coolants at Stagnation Temperatures from 1,295 Degrees Fahrenheit to 2,910 Degrees Fahrenheit (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of transpiration cooling has been conducted in the preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. The model consisted of a double wedge of 40 deg included angle having a porous stainless-steel specimen inserted flush with the top surface of the wedge. The tests were conducted at a free-stream Mach number of 2.0 for stagnation temperatures ranging from 1,295 F to 2,910 F. Nitrogen and helium were used as coolants and tests were conducted for values ranging from approximately 0.03 to 0.30 percent of the local weight flow rate. The data for both the nitrogen and helium coolants indicated greater cooling effectiveness than that predicted by theory and were in good agreement with the results for an 8 deg cone tested at a stagnation temperature of 600 F. The results indicate that the helium coolant, for the same amount of heat-transfer reduction, requires only about one-fourth to one-fifth the coolant flow weight as the nitrogen coolant.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TN-D-721 , L-1381
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  • 41
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    Constant Density Approximations for the Flow Behind Axisymmetric Shock Waves (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The incompressible rotational flow equations are used to obtain solutions for the flow behind axisymmetric shock waves with conic longitudinal sections. The nonlinear part of the term due to rotation is retained in the analysis. Numerical results for standoff distance and stagnation point velocity gradient are presented for the case in which the shock wave is a paraboloid, a sphere, or an oblate or prolate ellipsoid. A similarity parameter is proposed which correlates approximately the flow behind geometrically similar shock waves at different free-stream conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-857 , A-322
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  • 42
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    Numerical Solutions for Supersonic Flow of an Ideal Gas Around Blunt Two-Dimensional Bodies (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The method described is an inverse one; the shock shape is chosen and the solution proceeds downstream to a body. Bodies blunter than circular cylinders are readily accessible, and any adiabatic index can be chosen. The lower limit to the free-stream Mach number available in any case is determined by the extent of the subsonic field, which in turn depends upon the body shape. Some discussion of the stability of the numerical processes is given. A set of solutions for flows about circular cylinders at several Mach numbers and several values of the adiabatic index is included.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-791 , A-372
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  • 43
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    Measured Two-Dimensional Damping Effectiveness of Fuel-Sloshing Baffles applied to Ring Baffles in Cylindrical Tanks (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Measured two-dimensional damping forces of baffles with various shapes and perforations are presented for fluid conditions representative of those in liquid-fuel rocket vehicles. The effect of amplitude and frequency of fuel sloshing, and surface proximity on baffle damping are shown. Application of the result sin the prediction of damping effectiveness of ring baffles in cylindrical tanks is demonstrated. Finally, some measurements of damping in a free-free cylindrical tank are presented which verify the predictions based on two-dimensional results. Measurements of certain three-dimensional baffles show that they provide greater damping than ring baffles.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-694 , A-416
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  • 44
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    A Theoretical Analysis of Effects of Ablation on Heat Transfer to an Arbitrary Axisymmetric Body (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An analysis has been performed t o determine the effect of mass injection on heat transfer to an arbitrary surface of revolution. effective heat of ablation is determined, and the downstream effects of injection are investigated. It is found that the linear relation between heat of ablation and difference between wall and free-stream enthalpy, previously verified at the stagnation point, provides a useful approximation at any point on a surface of revolution. From the investigation of the downstream effects of injection it is found that an appreciable rate of heating may be obtained, even at points considerably downstream from the point at which injection ends. However, the radiation equilibrium temperature is proportional to the fourth root of the heating rate; therefore, except in particular cases, it will be difficult to make use of this effect in the design of thermal protection systems. Effects of radiation from a hot gas layer to the ablating surface are investigated by an approximate procedure. The efficiency of ablation is found to approach a maximum value which depends on the ratio of radiant heating to aerodynamic heating and is independent of the enthalpy difference across the boundary layer.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-741 , L-1198
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  • 45
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    Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 deg Cone in Free Flight at Supersonic Mach Numbers up to 5.9 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Measurements of aerodynamic heat transfer have been made at six stations on the 40-inch-long 10 deg. total-angle conical nose of a rocket- propelled model which was flight tested at Mach numbers up to 5.9. are presented for a range of local Mach number just outside the bound- ary layer on the cone from 1.57 to 5.50, and a range of local Reynolds number from 6.6 x 10(exp 6) to 55.2 x 10(exp 6) based on length from the nose tip.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-745 , L-1539
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  • 46
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    Experimental Investigation of an Air-Cooled Turbine Operating in a Turbojet Engine at Turbine Inlet Temperatures up to 2500 F (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An experimental investigation was made of an air-cooled turbine at average turbine inlet temperatures up to 2500 F. A modified production-model 12-stage axial-flow-compressor turbojet engine operating in a static sea-level stand was used as the test vehicle. The modifications to the engine consisted of the substitution of special combustor and turbine assemblies and double-walled exhaust ducting for the standard parts of the engine. All of these special parts were air-cooled to withstand the high operating temperatures of the investigation. The air-cooled turbine stator and rotor blades were of the corrugated-insert type. Leading-edge tip caps were installed on the rotor blades to improve leading-edge cooling by diverting the discharge of coolant to regions of lower gas pressure toward the trailing edge of the blade tip. Caps varying in length from 0.15- to 0.55-chord length were used in an attempt to determine the optimum cap length for this blade. The engine was operated over a range of average turbine inlet temperatures from about 1600 to about 2500 F, and a range of average coolant-flow ratios of 0.012 to 0.065. Temperatures of the air-cooled turbine rotor blades were measured at all test conditions by the use of thermocouples and temperature-indicating paints. The results of the investigation indicated that this type of blade is feasible for operation in turbojet engines at the average turbine inlet temperatures and stress levels tested(maximums of 2500 F and 24,000 psi, respectively). An average one-third-span blade temperature of 1300 F could be maintained on 0.35-chord tip cap blades with an average coolant-flow ratio of about 0.022 when the average turbine inlet temperature was 2500 F and cooling-air temperature was about 260 F. All of the leading-edge tip cap lengths improved the cooling of the leading-edge region of the blades, particularly at low average coolant-flow ratios. At high gas temperatures, such parts as the turbine stator and the combustor liners are likely to be as critical as the turbine rotor blades.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TN-D-1046 , E-1163
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  • 47
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    Existence of Solutions of One-Dimensional Flow of a Real Gas (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Formal solutions to the equations of motion of the one-dimensional, unsteady flow of a viscous, compressible, heat-conducting gas are presented. The relationship between the existence of these solutions and the problem of hydrodynamic stability is discussed.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: The Physics of Fluids; 4; 3; 360-361
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  • 48
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    Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of About 3.8 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static and total-pressure fluctuations were measured in the transonic flow region. A total pressure recovery of about 90 percent was obtained with a boundary-layer-removal mass flow rate of 15 percent of the inlet mass flow rate. The accompanying root-mean-square total pressure fluctuation in the throat region was only 1 percent of the free stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 x 10(exp 6).
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-854 , A-405
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  • 49
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    Ionization and Deionization Processes in Low-Density Plasma Flows (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Various plasma relaxation processes that are significant in laboratory plasma flows for aerospace physics studies are discussed on the basis of a survey of time decay studies of immobile plasmas. Some of the problems analyzed and discussed are: the relative importance of the various recombination mechanisms, catalytic deionization by electro- negative particles, delayed ionization produced by metastable action, and heating of the flow by deionization reactions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-740 , L-1369
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  • 50
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    The Flow Field over Blunted Flat Plates and its Effect on Turbulent Boundary-Layer Growth and Heat Transfer at a Mach Number of 4.7 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Surface pressures, impact and static pressure distributions in the flow field over the plate, and local heating rates were measured on a flat plate with various leading-edge diameters. The tests were conducted at a Mach number of 4.7 and a free-stream Reynolds number of 3.8 x 10(exp 6) per foot.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-689 , A-366
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  • 51
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    Charts for Conical and Two-Dimensional Oblique-Shock Flow Parameters in Helium at Mach Numbers from About 1 to 100 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Charts are presented for the determination of certain flow properties in the flow properties in the flow field and on the surface of cones and wedges at Mach numbers from about 1 to 100 in a perfect gas wigh a ratio of specific heats of 5/3. In addition, a table of the isentropic subsonic flow parameters is included.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-819 , L-244
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  • 52
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    A field report on the Alaska earthquakes of April 7, 1958 (1960)
    In:  Bull. Seism. Soc. Am., London, Army Corps of Engineers, Woodward-Clyde Consultants, vol. 50, no. 5485, pp. 489-510, pp. 1013, (ISBN: 0-12-018847-3)
    Details
    Publication Date: 1960
    Keywords: Earthquake ; Structural geology ; Seismicity ; seismicity ; BSSA
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  • 53
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    Major and great earthquakes of 1958 (1960)
    In:  Bull. Seism. Soc. Am., Rome, Academic Press, vol. 50, no. 6, pp. 323, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1960
    Keywords: Seismology ; Seismicity ; Earthquake catalog ; BSSA
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  • 54
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    The theory of the dislocation processes and its application to the Pacific region (1960)
    In:  Bull. Seism. Soc. Am., Luxembourg, Pergamon, vol. 50, no. 11, pp. 57-70, pp. L04605, (ISBN 1-86239-117-3)
    Details
    Publication Date: 1960
    Keywords: Dislocation ; Seismicity ; Tectonics ; BSSA
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  • 55
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    Earthquakes in North America (1960)
    Simon and Schuster
    In:  Bull., Polar Proj. OP-O3A4, Smithsonian treasure of science, New York, Simon and Schuster, vol. 2, no. XVI:, pp. 379-397, (ISBN: 3-540-23712-7)
    Details
    Publication Date: 1960
    Keywords: Seismology ; Seismicity
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  • 56
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    Radiation and Ablation Cooling for Manned Reentry Vehicles (1960)
    In:  CASI
    Details
    Publication Date: 2015-02-18
    Description: The necessity of reducing heat transfer to reentry vehicles has led I to the consideration of both radiative and ablation shields. The paper reviews briefly the heating problems for manned vehicles and the means whereby ablation and radiation afford thermal protection. The principal energy disposal and weight parameters are then presented and their relation to the vehicle and trajectory parameters is discussed. A comparative analysis of three types of ablation shield is made and broad conclusions are drawn as to the type of shield most appropriate to manned reentry vehicles.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 57
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    Application of Variational Methods to the Thermal Entrance Region of Ducts (1960)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: A variational method is presented for solving eigenvalue problems which arise in connection with the analysis of convective heat transfer in the thermal entrance region of ducts. Consideration is given, to both situations where the temperature profile depends upon one cross-sectional coordinate (e.g. circular tube) or upon two cross-sectional coordinates (e.g. rectangular duct). The variational method is illustrated and verified by application to laminar heat transfer in a circular tube and a parallel-plate channel, and good agreement with existing numerical solutions is attained. Then, application is made to laminar heat transfer in a square duct as a check, an alternate computation for the square duct is made using a method indicated by Misaps and Pohihausen. The variational method can, in principle, also be applied to problems in turbulent heat transfer.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: International Journal of Heat and Mass Transfer ; Volume 1; 161-172
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  • 58
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    Limitations of the Reflected-Shock Technique for Studying Fast Chemical Reactions (1960)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Journal of Chemical Physics; Volume 33; No. 1; 307-308
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  • 59
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    The Effect of a Deceleration Force on a Melting Boundary Layer (1960)
    In:  Other Sources
    Details
    Publication Date: 2018-06-05
    Description: Most analytical studies of ablating layers which melt before they vaporize have been restricted to the stagnation region of bodies (e.g., see Sutton). To determine conditions all along the body, it is important to include the deceleration force that opposes the downstream flow of liquid. Some treatment has already been given to this problem, but it is rather limited because of the idealization of the considered configuration or the omission of some important features of the problem. This note gives a more general discussion of the phenomena that occur when a body force acts on a melting boundary layer. The basis for these remarks is an analysis of the flow of a material like Pyrex over a two-dimensional body. The liquid density, specific heat, and conductivity are assumed constant. To determine the conditions under which deceleration effects are important and to simplify the basic equations, all variables except velocity and time are made dimensionless in the usual way.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Journal of the Aerospace Sciences; Volume 27; No. 8; 626-627
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  • 60
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    Heat-Transfer Coefficients for a Full-Scale Pebble-Bed Heater (1960)
    In:  Other Sources
    Details
    Publication Date: 2018-06-05
    Description: Large quantities of high-temperature air are needed for work with hypersonic flight problems. At temperatures above 2500 degrees Reamur, where conventional heat exchangers have exceeded their material limits, regenerative pebble-bed exchangers may be used with high-temperature refractories. The design of such a heat exchanger requires the use of reliable heat-transfer coefficients for a packed bed. Considerable data are available on the subject, but they spread over two orders of magnitude at any one Reynolds number value. The facility from which the present data were obtained is used at the Lewis Research Center (NASA) for testing air-breathing engine components. The purpose of this work was to obtain heat-transfer data during the initial operation of the bed as a guide to the design of similar equipment. The facility was designed with a conservative estimate of the heat-transfer coefficient, and is shown schematically. Temperatures throughout the packing were measured continuously so that point values of the coefficient might be obtained.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Industrial & Engineering Chemistry ; Volume 52; No. 5 ; 433-434
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  • 61
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    Joint Conference on Lifting Manned Hypervelocity and Reentry Vehicles. Part 2: a Compilation of the Papers Presented (1960)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-67562
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  • 62
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    Joint Conference on Lifting Manned Hypervelocity and Reentry Vehicles. Part 1: a Compilation of the Papers Presented (1960)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-67563
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  • 63
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    Heat Transfer to Longitudinal Laminar Flow Between Cylinders (1960)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Consideration is given to the fully developed heat transfer characteristics for longitudinal laminar flow between cylinders arranged in an equilateral triangular array. The analysis is carried out for the condition of uniform heat transfer per unit length. Solutions are obtained for the temperature distribution, and from these, Nusselt numbers are derived for a wide range of spacing-to-diameter ratios. It is found that as the spacing ratio increases, so also does the wall-to-bulk temperature difference for a fixed heat transfer per unit length. Corresponding to a uniform surface temperature around the circumference of a cylinder, the circumferential variation of the local heat flux is computed. For spacing ratios of 1.5 - 2.0 and greater, uniform peripheral wall temperature and uniform peripheral heat flux are simultaneously achieved. A simplified analysis which neglects circumferential variations is also carried out, and the results are compared with those from the more exact formulation.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: E-275
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    A Lunar Exploration Program Based upon Saturn-boosted Systems (1960)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-CR-133659 , DV-TR-2-60
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  • 65
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    A Radiant Heater to Simulate Aerodynamic Heating in a Wind Tunnel (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A recently developed radiant-heating test technique for simulation of aerodynamic heating in wind tunnel is describes. The heating device, which utilized quartz-tube lamps, was operated successfully while exposed directly to a supersonic airstream. Tests were made on a calibration panel, and experimental temperature and pressure data are presented. Results indicate that initial heating rates of about 26 Btu/(sq ft) (sec) are obtainable at a distance of 12 inches from the heater. Further applications of the basic design are discussed briefly.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA/TN-D-530 , L-917
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    Experimental Investigation of the Natural Frequencies of Liquids in Toroidal Tanks (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: Several toroidal configurations applicable to missile and space-vehicle liquid storage systems were oscillated to study the natural frequencies of the antisymmetric modes of contained liquids over a range of liquid depths and tank sizes. Natural frequencies for tank oscillations parallel to the free surface of both vertical and horizontal tank orientations. Natural frequencies were obtained. The data are presented in terms of dimensionless parameters which are obtained by relating experimentally determined natural liquid frequencies to analytical expressions developed through consideration of the physics of the problem and from existing solutions for liquids in tanks having similar boundaries at the liquid surface. The experimental results obtained for the toroids indicate that these parameters are applicable to the prediction of the natural frequencies of fluids in toroids of general geometry and size.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-531 , L-1069
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    Factors that Affect Operational Reliability of Turbojet Engines (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The problem of improving operational reliability of turbojet engines is studied. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TR-R-54
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    Static Thrust of an Annular Nozzle with a Concave Central Base (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TN-D-418 , L-851
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  • 69
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    Internal-Performance Evaluation of Two Fixed-Divergent-Shroud Ejectors (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Ejectors designed for use in a Mach 2.2 aircraft were evaluated over a range of representative primary pressure ratios and ejector corrected weight-flow ratios. Basic thrust and pumping characteristics are discussed in terms of an assumed engine operating schedule to illustrate the variation of performance with Mach number. The two designs differed about 16 percent in the shroud longitudinal spacing ratio. For corrected ejector weight-flow ratios up to 0.10, the performance of the fixed-shroud ejector designs is comparable with that of a similar continuously variable ejector except at conditions corresponding to acceleration with afterburning from Mach 0.4 to 1.2. In this region, the ejector thrust ratio decreased to a minimum of 0.96.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-257 , E-691
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  • 70
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    A Visual Technique for Determining Qualitative Aerodynamic Heating Rates on Complex Configurations (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An experimental investigation was conducted at a test-section Mach number of 4.95 and a stagnation temperature of 400 F to evaluate a visual technique for obtaining qualitative aerodynamic heat-transfer data on complex configurations.This technique utilized a temperature-sensetive paint indicated that this technique was satisfactory for determining qualitative heat-transfer rates on various bodies, some of which exhibited complex flow patterns. The results obtained have been found useful to guide the instrumentation of quantitative heat-transfer models, to supplement quantitative heat-transfer measurements, and to make preliminary heat-transfer studies for new configurations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-385 , L-662
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    Comparison of Theoretical and Experimental Values for the Effective Heat of Ablation of Ammonium Chloride (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Thermodynamic properties of ammonium chloride have been obtained and applied to a theoretical analysis of the shielding mechanism which reduces the rate of heat transfer to a body when ablation takes place at the surface. The analysis has considered the mechanism as one in which the material sublimes directly from the solid to the vapor phase. The results of the computation are compared with the experimental results obtained from the Langley 700-kilowatt arc jet.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-553 , L-843
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  • 72
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    Internal Performance Evaluation of a Two Position Divergent Shroud Ejector (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A two-position divergent shroud ejector was investigated in an unheated quiescent-air facility over a range of operational variables applicable to a Mach 2.5 aircraft. The performance data are shown in terms of hypothetical engine operating conditions to illustrate variations of performance with Mach number. The overall thrust performance was reasonably good, with ejector thrust ratios ranging from 0.97 to 0.98 for all conditions except that corresponding to acceleration with afterburning through the transonic flight Mach number region from 0.9 to 1.1, where the ejector thrust ratio decreased to as low as 0.945 for an ejector corrected weight-flow ratio of 0.105.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-258 , E-753
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  • 73
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    Larger shocks of 1948 (1949)
    California Institute of Technology Pasadena
    In:  Seismological Laboratory Bulletin, Milano, California Institute of Technology Pasadena, vol. 1948, no. 6, pp. 129, pp. L24306, (ISBN: 0534351875, 2nd edition)
    Details
    Publication Date: 1949
    Keywords: Earthquake catalog ; Seismology ; Seismicity
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  • 74
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    Earthquake study in Southern California 1948 (1949)
    In:  Trans., Am. Geophys. Union, Milano, California Institute of Technology Pasadena, vol. 30, no. 6, pp. 595-597, pp. L24306, (ISBN: 0534351875, 2nd edition)
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    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; EOS
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  • 75
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    In case of earthquake disaster (1949)
    American Red Cross, 2 pp.
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., American Red Cross, 2 pp., vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Earthquake precursor: prediction research
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  • 76
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    Seismicity of the earth and associated phenomena (1949)
    Princeton Univ. Press
    In:  Princeton, New Jersey, 7 + 273 pp., 1. ed., Princeton Univ. Press, vol. 34, no. XVI:, pp. 385-389, (ISBN 0-12-305355-2)
    Details
    Publication Date: 1949
    Keywords: Seismology ; Seismicity ; Textbook of geophysics
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  • 77
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    Two-Dimensional Motion of a Gas at Large Supersonic Velocities (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A large number of papers have been devoted to the problem of integration of equations of two-dimensional steady nonvertical adiabatic motion of a gas. Most of these papers are based on the application of the hodograph method of S. A. Chaplygin in which the plane of the hodograph of the velocity is taken as the region of variation of the independent variables in the equations of motion; the equations become linear in this plane. The exact integration of these equations is, however, obtained in the form of infinite series containing hypergeometric functions. The obtaining of such solutions and their investigation involves extensive computations. As a result, methods have been developed for the approximate integration of the equations of motion first transformed to a linear form. S. A. Chaplygin first pointed out such an approximate method applicable to flows in which the Mach number does not exceed 0.4.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1239 , Prikladnaia Matematika I Mekhanika, Tom XI
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  • 78
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    A Class of De Laval Nozzles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A study is made herein of the irrotational adiabatic motion of a gas in the transition from subsonic to supersonic velocities. A shape of the de Laval nozzle is given, which transforms a homogeneous plane-parallel flow at large subsonic velocity into a supersonic flow without any shockwaves beyond the transition line from the subsonic to the supersonic regions of flow. The method of solution is based on integration near the transition line of the gas equations of motion in the form investigated by S. A. Christianovich.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1236 , Prikladnaia Matematika I Mekhanika, Tom XI
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  • 79
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    The Characteristics Method Applied to Stationary Two-Dimensional and Rotationally Symmetrical Gas Flows (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: By means of characteristics theory, formulas for the numerical treatment of stationary compressible supersonic flows for the two-dimensional and rotationally symmetrical cases have been obtained from their differential equations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1211 , ZWB Forschungsbericht; Rept-1581
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  • 80
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    Altitude-Test-Chamber Investigation of Mcdonnell Afterburner on J34 Engine (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An altitude-test-chamber investigation was conducted to determine the operational and performance characteristics of a McDonnell afterburner with a fixed-area exhaust nozzle on a J34 engine. At rated engine speed, the altitude limit, as determined by combustion blow-out, occurred as a band of unstable operation of about 6000-foot altitude in width with minimum altitude limits from 31,000 feet at a simulated flight Mach number of 0.40 to about 45,500 feet at a simulated flight Mach number of 1.00. Considerable difficulty was experienced in attempting to establish or maintain balanced-cycle engine operation at altitudes above 36,000 feet. The fuel-air ratio for balanced-cycle operation and lean blowout of the afterburner, the augmented-thrust ratio, the total specific fuel consumption, and the afterburner combustion efficiency for balanced-cycle operation are summarized in a table. Satisfactory afterburner ignition was obtained over a range of flight Mach Numbers from 0.32 to 0.60 at altitudes from 10,000 to 30,000 and engine speeds from 10,000 to 12,500 rpm.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9D19
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  • 81
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    Heat Transfer from High-Temperature Surfaces to Fluids III - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperatures up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA/RM-E9D12
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  • 82
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    Calculation of Counterrotating Propellers (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A method for calculation of a counterrotating propeller which is similar to Walchner's method for calculation of the single propeller in the free air stream is developed and compared with measurements. Several dimensions which are important for the design are given end simple formulas for the gain in efficiency derived. Finally a survey of the behavior of the propeller for various operating conditions is presented.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1208 , ZWB Forschungsbericht Nr. 1752
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  • 83
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    On Wind Tunnel Tests and Computations Concerning the Problem of Shrouded Propellers (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Results of measurements on a shrouded propeller are given. The propeller is designed for the high ratio of advance and high thrust loading. The effect of the shape of propeller and shroud upon the aerodynamic coefficients of the propulsion unit can be seen from the results. The highest efficiency measured is 0.71. The measurements permit the conclusion that the maximum efficiency can be essentially improved by shroud profiles of small chord and thickness. The largest static thrust factor of merit measured reaches according to Bendemann, a value of about zeta = 1.1. By the use of a nose split flap the static thrust for thin shroud profiles with small nose radius can be about doubled. In a separate section numerical investigations of the behavior of shrouded propellers for the ideal case and for the case with energy losses are carried out. The calculations are based on the assumption that the slipstream cross section depends solely on the shape of the shroud and not on the propeller loading. The reliability of this hypothesis is confirmed experimentally and by flow photographs for a shroud with small circulation. Calculation and test are also in good agreement concerning efficiency and static thrust factor of merit. The prospects of applicability for shrouded propellers and their essential advantages are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1202
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  • 84
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    Experimental study of flow past turbine blades (1949)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The requirements on gas turbines for aircraft power units, namely, adequate efficiency, operation at high gas temperatures, low weight, and small dimensions, must be taken into consideration during the design of the blading. To secure good efficiency, it is necessary that the gas flow past the blades as smoothly as possible without separation. This is relatively easily obtainable in the accelerated flow of turbine blading, if the blade spacing is chosen small enough. A small blade spacing, however, is detrimental to the other requirements outlined above. Operation at high gas temperatures usually calls for blade cooling. This cooling is associated with a power input that lowers the turbine efficiency. Since the amount of heat that must be carried off for coding a blade can be influenced rather little, the gross power input for a turbine stage can be reduced by keeping the number of blades to a minimum, that is, with blades of high spacing ratio. But here also a limit is imposed, the exceeding of which is followed by separation of flow. Hence the requirement of finding blade forms on which the flow separates at rather high spacing ratios .
    Keywords: Aircraft Propulsion and Power
    Type: NACA-TM-1209
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    Behavior of the Laminar Boundary Layer for Periodically Oscillating Pressure Variation (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The calculation of the phenomena within the boundary layer of bodies immersed in a flow underwent a decisive development on the basis of L. Prandtl's trains of thought, stated more than forth years ago, and by numerous later treatises again and again touching upon them. The requirements of the steadily improving aerodynamics of airplanes have greatly increased with the passing of time and recently research became particularly interested in such phenomena in the boundary layer as are caused by small external disturbances. Experimental results suggest that, for instance, slight fluctuations in the free stream velocities as they occur in wind tunnels or slight wavelike deviations of outer wing contours from the prescribed smooth course as they originate due to construction inaccuracies may exert strong effects on the extent of the laminar boundary layer on the body and thus on the drag. The development of turbulence in the last part of the laminar portion of the boundary layer is, therefore, the main problem, the solution of which explains the behavior of the transition point of the boundary layer. A number of reports in literature deal with this problem,for instance, those of Tollmien, Schlichting, Dryden, and Pretsch. The following discussion of the behavior of the laminar boundary layer for periodically oscillating pressure variation also purports to make a contribution to that subject.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1228 , Ludwig Prandtl zum 70. Geburtstage, Schriften der Deutschen Akademie der Luftfahrtforschung, Publications of the Germany academy for Aviation Research; 247-255
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  • 86
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    Rotationally Symmetric Potential Flows (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: This paper includes the following topics: 1) Characteristic differential equations; 2) Treatment of practical examples; 3) First example: Diffuser; and 4) Second Example: Nozzle.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1244 , Chapter 4, Technische Hoschschule Dresden, Archives No. 44; Rept-44/4
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  • 87
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    Performance of Axial-Flow Supersonic Compressor of XJ55-FF-1 Turbojet Engine (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An investigation was conducted to determine the performance characteristics of the rotor and inlet guide vanes used in the axial-flow supersonic compressor of the XJ55-FF-1 turbojet engine. Outlet stators used in the engine were omitted to facilitate study of the supersonic rotor. The extent of the deviation from design performance indicates that the design-shock configuration was not obtained. A maximum pressure ratio of 2.26 was obtained at an equivalent tip speed of 1614 feet per second and an adiabatic efficiency of 0.61. The maximum efficiency obtained was 0.79 at an equivalent tip speed of 801 feet per second and a pressure ratio of 1.29. The performance obtained was considerably below design performance. The effective aerodynamic forces encountered appeared to be large enough to cause considerable damage to the thin aluminum leading edges of the rotor blades.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9G19
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  • 88
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    Performance of J33-A-21 and J33-A-23 Turbojet-Engine Compressors with Water Injection (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: As part of the performance investigation of compressors for the J33 turbojet engine, the A-21 model and the A-23 model with a 17- and a 34-blade impeller were operated with water injection at their respective design equivalent speeds of 11,500 and 11,750 rpm. Inlet conditions of pressure of 14 inches of mercury absolute and of ambient temperature correspond to those of the investigation of these models without water injection. The water-air ratio by weight ranged from 0.05 to 0.06. By the use of water injection, the peak pressure ratio of the A-21 compressor and the A-23 compressor with a 34-blade impeller increased approximately 0.38, whereas that of the A-23 compressor with a 17-blade impeller increased only 0.14. The decrease in maximum efficiency for the three compressors ranged from 0.12 to 0.14. The highest increase in maximum equivalent weight flow of air plus weight flow of water was 10.90 pounds per second obtained with the A-21 compressor. The increase in air weight flow alone was approximately 5.70 pounds per second for the A-21 compressor end the A-23, 17-blade compressor, which exceeded the increase of 3.15 pounds per second for the A-23; 34-blade compressor.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9G13
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  • 89
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    Report on Investigation of Developed Turbulence (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The recent experiments by Jakob and Erk, on the resistance of flowing water in smooth pipes, which are in good agreement with earlier measurements by Stenton and Pannell, have caused me to change my opinion that the empirical Blasius law (resistance proportional to the 7/4 power of the mean velocity) was applicable up to arbitrarily high Reynolds numbers. According to the new tests the exponent approaches 2 with increasing Reynolds number, where it remains an open question whether or not a specific finite limiting value of the resistance factor lambda is obtained at R = infinity. With the collapse of Blasius' law the requirements which produced the relation that the velocity in the proximity of the wall varied in proportion to the 7th root of the wall distance must also become void. However, it is found that the fundamental assumption that led to this relationship can be generalized so as to furnish a velocity distribution for any empirical resistance law. These fundamental assumptions can be so expressed that for the law of velocity distribution in proximity of the wall as well as for that of friction at the wall, a form can be found in which the pipe diameter no longer occurs, or in other words, that the processes in proximity of a wall are not dependent upon the distance of the opposite wall.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1231 , Zeitschrift fuer Angewandte Matematik und Mechanik; 5; 2; 136-139
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  • 90
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    Lift Force of an Arrow-Shaped Wing (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The flow about a conical body of an ideal compressible fluid is considered. Assume that the velocity of the oncoming flow at infinity W is directed along the z-axis. The system of Cartesian coordinates x, y, z with origin at the vertex of the cone O is shown. From the considerations,of the dimensional theory, it may be found that along any ray issuing from O the components of the velocity u, v, W+w along the coordinate axes will maintain a constant value. It is further assumed that the conical body has such shape and disposition relative to the flow that u, v, and w are small in comparison with W.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1245 , Prikladnaya Matematika I Mekhanika; X; 513-520
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  • 91
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    Gas Motion in a Local Supersonic Region and Conditions of Potential-Flow Breakdown (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: For a certain Mach number of the oncoming flow, the local velocity first reaches the value of the local velocity of sound (M = 1) at some point on the surface of the body located within the flow. This Mach number is designated the critical Mach number M(sub cr). By increasing the flow velocity, a supersonic local region is formed bounded by the body contour and the line of transition from subsonic to supersonic velocity. As is shown by observations with the Toepler apparatus, at a certain flow Mach number M 〉 M(sub cr) a shock wave is formed near the body that closes the local supersonic region from behind. The formation of the shock wave is associated with the appearance of an additional resistance defined as the wave drag. In this paper, certain features are described of the flow in the local supersonic region, which is bounded by the contour of the body and the transition line, and conditions are sought for which the potential flow with the local supersonic region becomes impossible and a shock wave occurs. In the first part of the paper, the general properties of the potential flow in the local supersonic region, bounded by the contour of the profile and the transition line, are established. It is found that at the transition line, if it is not a line of discontinuity, the law of monotonic variation of the angle of inclination of the velocity vector holds (monotonic law). An approximation is given for the change in velocity at the contour of the body. The flow about a contour having a straight part is studied. In the second part of the paper, an approximation is given of the magnitudes of the accelerations at the interior points of the supersonic region. With the aid of these approximations, it is shown that for profiles convex to the flow the breakdown of the potential flow,associated with an increase of the Mach number of the oncoming flow, cannot be due to the formation of an envelope of the characteristics within the supersonic region. On the basis of the monotonic law, the transitional Mach number M is found, beyond which the potential flow with local supersonic region becomes impossible.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1213 , Prikladnaya Matematika i Mekhanika; 10; 4; 481-502
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  • 92
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    On the Theory of the Laval Nozzle (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In the present paper, the motion of a gas in a plane-parallel Laval nozzle in the neighborhood of the transition from subsonic to supersonic velocities is studied. In a recently published paper, F. I. Frankl, applying the holograph method of Chaplygin, undertook a detailed investigation of the character of the flow near the line of transition from subsonic to supersonic velocities. From the results of Tricomi's investigation on the theory of differential equations of the mixed elliptic-hyperbolic type, Frankl introduced as one of the independent variables in place of the modulus of the velocity, a certain specially chosen function of this modulus. He thereby succeeded in explaining the character of the flow at the point of intersection of the transition line and the axis of symmetry (center of the nozzle) and in studying the behavior of the stream function in the neighborhood of this point by separating out the principal term having, together with its derivatives, the maximum value as compared with the corresponding corrections. This principal term is represented in Frankl's paper in the form of a linear combination of two hypergeometric functions. In order to find this linear combination, it is necessary to solve a number of boundary problems, which results in a complex analysis. In the investigation of the flow with which this paper is concerned, a second method is applied. This method is based on the transformation of the equations of motion to a form that may be called canonical for the system of differential equations of the mixed elliptic-hyperbolic type to which the system of equations of the motion of an ideal compressible fluid refers. By studying the behavior of the integrals of this system in the neighborhood of the parabolic line, the principal term of the solution is easily separated out in the form of a polynomial of the third degree. As a result, the computation of the transitional part of the nozzle is considerably simplified.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1212 , Prikladnaya Matematika I Mekhanika; 10; 4; 503-512
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    Contribution to the Problem of Flow at High Speed (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The authors regret that due to the lack of time the investigations could not be carried out to a more finished form. Especially in the first part it was intended to include a few further applications and to use them in the general considerations of this part. In spite of the fact that the intentions of the authors could not be realized, the authors felt that it would serve the aims of the competition to present part I in its present fragmentary form. The topics include: 1) A Few General Remarks Covering the Prandtl-Busemann Method; and 2) Effect of Compressibility in Axially Symmetrical Flow around an Ellipsoid.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1233 , Lilienthal-Gesellschaft fuer Luftfahrtforschung Bericht S 13/1, Part 1; 40-68; Rept-13/1
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  • 94
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    Heat Transmission in the Boundary Layer (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: In the present paper which deals with the heat transfer between the gas and the wall for large temperature drops and large velocities use is made of the method of Dorodnitsyn of the introduction of a new independent variable, with this difference, however, that the relation between the temperature field (that is, density) and the velocity field in the general case considered is not assumed given but is determined from the solution of the problem. The effect of the compressibility arising from the heat transfer is thus taken into account (at the same time as the effect of the compressibility at the large velocities). A method is given for determining the coefficients of heat transfer and the friction coefficients required in many technical problems for a curved wall in a gas flow at large Mach numbers and temperature drops. The method proposed is applicable both for Prandtl number P = 1 and for P not equal to 1.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1229 , Prikladnaya Matematika I Mekhanika, Tom X; 449-474
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  • 95
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    Flow Measurement by Means of Light Interference (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: There has been under development for the high-speed wind tunnel of the LFA an optical measuring arrangement for the qualitative and quantitative investigation of flow. By the use of interference measurements, the determination of density at the surface of the bodies being tested in the air stream and in the vicinity of these bodies can be undertaken. The results obtained so far in the simple preliminary investigations show that it is possible, even at a low Reynolds number, to obtain the density field in the neighborhood of a test body by optical means. Simple analytical expressions give the relation between density, pressure, velocity, and temperature. In addition to this, the interference measurement furnishes valuable data on the state of the boundary layer, that is, the sort of boundary layer (whether laminar or turbulent), as well as the temperature and velocity distribution.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1253 , Forschungsbericht; Rept-1167
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  • 96
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    Boundary Layer Theory (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The flow laws of the actual flows at high Reynolds numbers differ considerably from those of the laminar flows treated in the preceding part. These actual flows show a special characteristic, denoted as turbulence. The character of a turbulent flow is most easily understood the case of the pipe flow. Consider the flow through a straight pipe of circular cross section and with a smooth wall. For laminar flow each fluid particle moves with uniform velocity along a rectilinear path. Because of viscosity, the velocity of the particles near the wall is smaller than that of the particles at the center. i% order to maintain the motion, a pressure decrease is required which, for laminar flow, is proportional to the first power of the mean flow velocity. Actually, however, one ob~erves that, for larger Reynolds numbers, the pressure drop increases almost with the square of the velocity and is very much larger then that given by the Hagen Poiseuille law. One may conclude that the actual flow is very different from that of the Poiseuille flow.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1218
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  • 97
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    Two-Dimensional Potential Flows (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Contents include the following: Characteristic differential equations - initial and boundary conditions. Integration of the second characteristic differential equations. Direct application of Meyer's characteristic hodograph table for construction of two-dimensional potential flows. Prandtl-Busemann method. Development of the pressure variation for small deflection angles. Numerical table: relation between deflection, pressure, velocity, mach number and mach angle for isentropic changes of state according to Prandtl-Meyer for air (k = 1.405). References.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1243 , Chapter 3,Technische Hochschule Dresden, Archives No. 44/3; Rept-44/3
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  • 98
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    Heat Transfer from High-Temperature Surfaces to Fluids. III - Correlation of Heat-Transfer Data for Air Flowing in Silicon Carbide Tube with Rounded Entrance, Inside Diameter of 3/4 Inch, and Effective Length of 12 Inches (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A heat-transfer investigation was conducted with air flowing through an electrically heated silicon carbide tube with a rounded entrance, an inside diameter of 3/4 inch, and an effective heat-transfer length of 12 inches over a range of Reynolds numbers up to 300,000 and a range of average inside-tube-wall temperature up to 2500 R. The highest corresponding local outside-tube-wall temperature was 3010 R. Correlation of the heat-transfer data using the conventional Nueselt relation wherein physical properties of the fluid were evaluated at average bulk temperature resulted in a separation of data with tube-wall-temperature level. A satisfactory correlation of the heat-transfer data was obtained, however, by the use of modified correlation parameters wherein the mass velocity G (or product of average air density and velocity evaluated at bulk temperature P(sub b)V(sub b)) in the Reynolds number was replaced by the product of average air velocity evaluated at the bulk temperature and density evaluated at either the average inside-tube-wall temperature or the average film temperature; in addition, all the physical properties of air were correspondingly evaluated at either the average inside-tube-wall temperature or the average film temperature.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-RM-E9D12-Pt-3 , Rept-1115-Pt-3
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  • 99
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    Performance of Single-Stage Turbine of Mark 25 Torpedo Power Plant with Two Special Nozzles (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: A single-stage modification of the turbine from a Mark 25 torpedo power plant was investigated to determine the performance with two nozzle designs in combination with special rotor blades having a 20 inlet angle. The performance is presented in terms of blade, rotor, and brake efficiency as a function of blade-jet speed ratio for pressure ratios of 8, 15 (design), and 20. The blade efficiency with the nozzle having circular pas- sages (K) was equal to or higher than that with the nozzle having rectangular passages (J) for all pressure ratios and speeds investigated. The maximum blade efficiency of 0.571 was obtained with nozzle K at a pressure ratio of 8 and a blade-jet speed ratio of 0.296. The difference in blade efficiency was negligible at a pressure ratio of 8 at the low speeds; the maxim difference was 0.040 at a pressure ratio of 20 and a blade-jet speed ratio of 0.260.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9H09
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  • 100
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    Performance of J33-A-27 Turbojet-Engine Compressor (1949)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-SE9F30
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