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  • AERODYNAMICS  (99)
  • SOLAR PHYSICS  (36)
  • FLUID MECHANICS AND HEAT TRANSFER
  • GENERAL
  • 1975-1979  (159)
  • 1955-1959
  • 1940-1944
  • 1979  (159)
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  • 1975-1979  (159)
  • 1955-1959
  • 1940-1944
Year
  • 1
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    On turbulence modeling for unsteady transonic flows (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A detailed examination of the turbulent field in an unsteady transonic flow undergoing shock-induced separation is conducted. Ensemble-averaged mean and fluctuating velocities, obtained from conditionally sampled laser velocimeter data, are described and analyzed to assess the applicability of modeling concepts usually employed in steady-flow problems. Some comparisons with computations employing the Reynolds averaged Navier-Stokes equations with a mixing length turbulence model are then presented to illustrate the status of current predictive capabilities. The results appear to imply that turbulence models developed for steady flows apply and that the model need not reflect all the fine details of the turbulent structure but rather account in an approximate way for the production and destruction of the turbulence.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 79-0071 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Investigations on transparent liquid-miscibility gap systems (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Sedimentation and phase separation is a well known occurrence in monotectic or miscibility gap alloys. Previous investigations indicate that it may be possible to prepare such alloys in a low-gravity space environment but recent experiments indicate that there may be nongravity dependent phase separation processes which can hinder the formation of such alloys. Such phase separation processes are studied using transparent liquid systems and holography. By reconstructing holograms into a commercial-particle-analysis system, real time computer analysis can be performed on emulsions with diameters in the range of 5 micrometers or greater. Thus dynamic effects associated with particle migration and coalescence can be studied. Characterization studies on two selected immiscible systems including an accurate determination of phase diagrams, surface and interfacial tension measurements, surface excess and wetting behavior near critical solution temperatures completed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Alabama Univ. UAH(NASA Workshop on Fluids Expt. System; p 21-35
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    NASA TECHNICAL REPORTS
  • 3
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    Pitot pressure measurements in flow fields behind circular-arc nozzles with exhaust jets at subsonic free-stream Mach numbers (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The flow field behind a circular arc nozzle with exhaust jet was studied at subsonic free stream Mach numbers. A conical probe was used to measure the pitot pressure in the jet and free stream regions. Pressure data were recorded for two nozzle configurations at nozzle pressure ratios of 2.0, 2.9, and 5.0. At each set of test conditions, the probe was traversed from the jet center line into the free stream region at seven data acquisition stations. The survey began at the nozzle exit and extended downstream at intervals. The pitot pressure data may be applied to the evaluation of computational flow field models, as illustrated by a comparison of the flow field data with results of inviscid jet plume theory.
    Keywords: AERODYNAMICS
    Type: NASA-TM-80169 , L-13060
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Average photospheric poloidal and toroidal magnetic field components near solar minimum (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Average (over longitude and time) photospheric magnetic field components are derived from 3-min Stanford magnetograms made near the solar minimum of cycle 21. The average magnetograph signal is found to behave as the projection of a vector for measurements made across the disk. The poloidal field exhibits the familiar dipolar structure near the poles, with a measured signal in the line Fe I 5250 A of about 1 G. At low latitudes the poloidal field has the polarity of the poles, but is of reduced magnitude (about 0.1 G). A net photospheric toroidal field with a broad latitudinal extent is found. The polarity of the toroidal field is opposite in the northern and southern hemispheres and has the same sense as subsurface flux tubes giving rise to active regions of solar cycle 21. These observations are used to discuss large-scale electric currents crossing the photosphere and angular momentum loss to the solar wind.
    Keywords: SOLAR PHYSICS
    Type: Solar Physics; 61; Mar. 197
    Format: text
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  • 5
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    An investigation of the 1.9 A feature in solar-flare X-ray spectra (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The 1.9 A feature, observed in the X-ray spectra of three solar flares with the Columbia University and Lockheed Palo Alto Research Laboratory spectrometers on the OSO 8 satellite, is shown to be due to a blend of 1s-2p transitions in a range of Fe ions. In the temperature range 9-16 x -10 to the 6th K, the feature has a mean wavelength of 1.900 + or - 0.009 A and is 0.04 A wider than a single line, indicating that the main contributors are Fe XIX-Fe XXII. Most of the emission originates from the dielectronic recombination process, and when inner-shell excitation is included together with normal collisional excitation, the observed intensity of the feature can be accounted for adequately. For these events, if the electron density is below approximately 10 to the 12th/cu cm, deviations from ionization equilibrium will be significant for ions more highly ionized than Fe XXI.
    Keywords: SOLAR PHYSICS
    Type: Astrophysical Journal; vol. 231
    Format: text
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  • 6
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    Bumblebee program: Aerodynamic data. Part 3: Pressure fields at Mach numbers 1.5 and 2.0 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A large amount of fundamental aerodynamic missile data, which were stored for a number of years at the Applied Physics Laboratory, are reported. Data that supplements the M = 2.0 flow field data are provided. The Mach number effect by means of pressure fields only, at M = 1.5 and 2.0, and at angles of attack up to 23 deg at a mid-body station where a wing might be located is described.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3116
    Format: application/pdf
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  • 7
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    Bumblebee program, aerodynamic data. Part 2: Flow fields at Mach number 2.0 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Available flow field data which can be used in validating theoretical procedures for computing flow fields around supersonic missiles are presented. Tabulated test data are given which define the flow field around a conical-nosed cylindrical body in a crossflow plane corresponding to a likely tail location. The data were obtained at a Mach number of 2.0 for an angle of attack of 0 to 23 degrees. The data define the flow field for cases both with and without a forward wing present.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3115
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  • 8
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    Flow friction of the turbulent coolant flow in cryogenic porous cables (1979)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Considered are cryogenic power transmission cables with porous cores. Calculations of the turbulent coolant flow with injection or suction through the porous wall are presented within the framework of a two-layer model. Universal velocity profiles were obtained for the viscous sublayer and flow core. Integrating the velocity profile, the law of flow friction in the pipe with injection has been derived for the case when there is a tangential injection velocity component. The effect of tangential velocity on the relative law of flow friction is analyzed. The applicability of the Prandtl model to the problem under study is discussed. It is shown that the error due to the acceptance of the model increases with the injection parameter and at lower Reynolds numbers; under these circumstances, the influence of convective terms in the turbulent energy equation on the mechanism of turbulent transport should be taken into account.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-79052 , DOE/NASA/0207-79/1 , Intern. Congr. on Refrigeration; Sep 23, 1979 - Sep 29, 1979; Venice; Italy
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  • 9
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    Advanced missile technology. A review of technology improvement areas for cruise missiles (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Technology assessments in the areas of aerodynamics, propulsion, and structures and materials for cruise missile systems are discussed. The cruise missiles considered cover the full speed, altitude, and target range. The penetrativity, range, and maneuverability of the cruise missiles are examined and evaluated for performance improvements.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3187 , BFD-0-79-001
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  • 10
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    Flight-measured afterbody pressure coefficients from an airplane having twin side-by-side jet engines for Mach numbers from 0.6 to 1.6 (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Afterbody pressure distribution data were obtained in flight from an airplane having twin side-by-side jet exhausts. The data were obtained in level flight at Mach numbers from 0.60 to 1.60 and at elevated load factors for Mach numbers of 0.60, 0.90, and 1.20. The test altitude varied from 2300 meters (7500 feet) to 15,200 meters (50,000 feet) over a speed range that provided a matrix of constant Mach number and constant unit Reynolds number test conditions. The results of the full-scale flight afterbody pressure distribution program are presented in the form of plotted pressure distributions and tabulated pressure coefficients with Mach number, angle of attack, engine nozzle pressure ratio, and unit Reynolds number as controlled parameters.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1549 , H-1066
    Format: application/pdf
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