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  • Inorganic Chemistry  (1,161)
  • AERODYNAMICS  (464)
  • INSTRUMENTATION AND PHOTOGRAPHY  (249)
  • Industrial Chemistry
  • Seismology
  • 2020-2024
  • 2000-2004
  • 1985-1989
  • 1975-1979  (1,475)
  • 1950-1954  (637)
  • 1976  (1,475)
  • 1954  (637)
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  • 2020-2024
  • 2000-2004
  • 1985-1989
  • 1975-1979  (1,475)
  • 1950-1954  (637)
Year
  • 1
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    In:  J. Geophys. Res., Bonn, Inst. f. Theoret. Geodäsie, vol. 81, no. 3-5, pp. 3036-3046, pp. B04102, (ISBN: 0-12-018847-3)
    Publication Date: 1976
    Keywords: Modelling ; Seismology ; Least-squares ; Hypocentral depth ; Velocity ; Velocity depth profile ; JGR
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  • 2
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    In:  Geophys. J. R. astr. Soc., Luxembourg, U.S. Geological Survey, vol. 44, no. 24, pp. 7-17, pp. B05309, (ISBN 0-471-26610-8)
    Publication Date: 1976
    Keywords: Travel time ; Seismology ; GJRaS ; Dziewonski
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  • 3
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    In:  Phys. Earth Plan. Int., Zagreb, Univ. Tokyo, vol. 12, no. 8, pp. 118-127, pp. L04601, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Seismology ; Seismic networks ; earth mantle ; Location ; PEPI
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  • 4
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    In:  Geophys. J. R. astr. Soc., New York, August, vol. 44, no. 1, pp. 595-599, pp. 1610, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Moment tensor ; Seismology ; Surface waves ; Source ; GJRaS
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  • 5
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    In:  Phys. Earth Plan. Int., London, Icelandic Meteorological Office, Ministry for the Environment University of Iceland, vol. 12, no. 4, pp. 291-318, pp. B02206, (ISSN 0016-8548, ISBN 3-510-50045-8)
    Publication Date: 1976
    Keywords: Seismology ; Statistical investigations ; Seismicity ; PEPI
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  • 6
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    In:  J. Geophys., Würzburg, Physica-Verlag, vol. 42, no. 1, pp. 191-200, pp. L24313, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Reflectivity ; Layers ; Seismology ; Reflectivity method
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  • 7
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    In:  Geophys. J. R. astr. Soc., L'wiw, Inst. f. Theoret. Geodäsie, vol. 47, no. 4, pp. 41-58, pp. B01408, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Dispersion ; Inelastic ; Seismology ; earth mantle ; GJRaS ; FROTH ; (abstract)
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  • 8
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    In:  Bull. Seism. Soc. Am., Tulsa, 3-4, vol. 66, no. 3-4, pp. 173-187, pp. B09405, (ISBN: 0-12-018847-3)
    Publication Date: 1976
    Keywords: Seismology ; Location ; AUD ; Hypocenter determination ; BSSA
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  • 9
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    In:  Bull. Seism. Soc. Am., Roma, Polish Geothermal Association, vol. 66, no. 2, pp. 1459-1484, pp. B05406, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: High frequency ... ; Data analysis / ~ processing ; Fault plane solution, focal mechanism ; Seismology ; BSSA
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  • 10
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    Springer Verlag
    In:  Professional Paper, Explosion Seismology in Central Europe,, Berlin, Springer Verlag, vol. 65, no. 16, pp. 62-72, (ISBN 1-86239-165-3, vi + 330 pp.)
    Publication Date: 1976
    Keywords: Nuclear explosion ; Seismology ; Discrimination
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  • 11
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    In:  Bulletin of the Seismological Society of America, Tokyo, Am. Geophys. Union, vol. 66, no. 6, pp. 2069-2074, pp. 8043
    Publication Date: 1976
    Keywords: Earthquake precursor: prediction research ; ethics ; Seismology ; society ; BSSA
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  • 12
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    In:  Bull. Seism. Soc. Am., Hannover, Bundesanstalt für Geowissenschaften und Rohstoffe, vol. 66, no. 40, pp. 1441-1457, pp. L08305
    Publication Date: 1976
    Keywords: Nuclear explosion ; Stress ; P-waves ; Seismology ; BSSA
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  • 13
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    In:  Bull. Seism. Soc. Am., Regensburg, Inst. Electrical & Electronics Engineers, vol. 66, no. 3, pp. 1801-1804, pp. TC5001, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1976
    Keywords: Body waves ; Stress drop ; Elasticity ; Seismology ; BSSA
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  • 14
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    In:  Geophys. J. R. astr. Soc., Bonn, South Afr. Inst. Mining Metall., vol. 47, no. 2, pp. 251-255, pp. 1056, (ISBN: 0534351875, 2nd edition)
    Publication Date: 1976
    Keywords: Seismology ; Moment tensor ; Deconvolution ; Seismic networks ; GJRaS
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  • 15
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    In:  Eos, Trans., Am. Geophys. Un., Dresden, H.-J. Vogt, vol. 57, no. 6, pp. 180-188
    Publication Date: 1976
    Keywords: Seismology ; Seismic networks
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  • 16
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    In:  Geologisches Jahrbuch Reihe E Geophysik - geophysics, San Francisco, Pergamon, vol. 116, no. E7, pp. 53-57, pp. 1246
    Publication Date: 1976
    Keywords: Planetology ; moon ; Scattering ; Seismology
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  • 17
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    In:  Bull. Seism. Soc. Am., Warszawa, Elsevier, vol. 66, no. 1, pp. 617-623, pp. 2091, (ISBN: 0-12-018847-3)
    Publication Date: 1976
    Keywords: Seismology ; BSSA
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  • 18
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    In:  Phys. Earth Plan. Int., Darmstadt, Wissenschaftliche Buchgesellschaft, vol. 12, no. 3-4, pp. 329-342, pp. L11308, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Nuclear explosion ; Seismology ; Detectors ; Magnitude ; Seismic networks ; PEPI
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  • 19
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    Cambridge Univ. Press
    In:  Cambridge, 6th Edition, 574 pp., Cambridge Univ. Press, vol. 46, no. XVI:, pp. 1-14, (ISBN: 0-387-30752-4)
    Publication Date: 1976
    Keywords: Textbook of geophysics ; Seismology ; Earth model, also for more shallow analyses ! ; Geol. aspects ; Physical properties of rocks
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  • 20
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    In:  Bull. Seism. Soc. Am., Houston, Akademie-Verlag, vol. 66, no. 6, pp. 1953-1964, pp. L08310, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Seismology ; Teleseismic events ; Seismic arrays ; Schafer ; BSSA
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  • 21
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    Am. Geophys. Union
    In:  Bull., Open-File Rept., Geodynamics: Progress and Prospects, Washington D. C., Am. Geophys. Union, vol. 65, no. 1, pp. 171-1883, (ISBN 0080419208)
    Publication Date: 1976
    Keywords: Seismology ; Tectonics ; Crustal deformation (cf. Earthquake precursor: deformation or strain)
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  • 22
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    In:  Phys. Earth Plan. Interiors, Kyoto, AGU, vol. 12, no. B1, pp. 319-328, pp. L24302, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Seismology ; Surface waves ; Fracture ; Earthquake ; PEPI
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  • 23
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    In:  Bull. Seism. Soc. Am., New York, Scientific American, vol. 66, no. Nov., pp. 979-985, pp. B10302, (ISSN: 1340-4202)
    Publication Date: 1976
    Keywords: Seismology ; Instruments ; Detectors ; BSSA
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  • 24
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    W. H. Freeman
    In:  San Francisco, W. H. Freeman, vol. 17, pp. 225, (ISBN 0-19-851393-3)
    Publication Date: 1976
    Keywords: GEOBIB:MB ; 2685 ; Seismology ; Nuclear explosion
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  • 25
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    Deutsche Forschungsgemeinschaft & boldt druck
    In:  DFG-Forschungsbericht, im Auftr. der Senatskommission für geowissenschaftliche Gemeinschaftsforschung, Boppard, Deutsche Forschungsgemeinschaft & boldt druck, vol. C 560, 183 pp., no. 29, pp. 1058-1061, (ISBN 3-933346-037)
    Publication Date: 1976
    Keywords: Seismology ; Proceedings of a conference
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  • 26
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    US Department of the Interior, Geological Survey
    In:  Open File Report, Menlo Park, California, US Department of the Interior, Geological Survey, vol. 10, no. 77-3, pp. 241-244, (ISBN 3-933346-037)
    Publication Date: 1976
    Keywords: Seismology ; Micro seismicity ; Seismic networks ; USGS
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  • 27
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    Institut f. Meteorol. und Geophys., Univ. Frankfurt/Main
    In:  Dissertation, Berichte, Granada, 10-12 June 1999, Institut f. Meteorol. und Geophys., Univ. Frankfurt/Main, vol. 339-350, no. 32, pp. 103-108, (ISBN 3-933346-037)
    Publication Date: 1976
    Keywords: Seismology ; Source ; Fracture ; Stockl
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  • 28
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    In:  CASI
    Publication Date: 2010-11-08
    Description: Prandtl's theory is used to determine the airflow over bodies and wings adapted to supersonic flight. By making use of these results, and by incorporating in them an allowance for the probable skin friction, some estimates of expected lift-drag ratios are made for various flight speeds with the best configuration. At each speed a slender body and wings having the best angle of sweepback are considered. For the range of supersonic speeds shown an airplane of normal density and loading would be required to operate at an altitude of the order of 60,000 feet. The limiting value of 1-1/2 times the speed of sound corresponds to a flight speed of 1000 miles per hour. At this speed about 1.5 miles per gallon of fuel are expected. It is interesting to note that this value corresponds to a value of more than 15 miles per gallon when the weight is reduced to correspond to that of an ordinary automobile.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 499-514
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  • 29
    Publication Date: 2010-11-08
    Description: In theory, the most efficient wing shape for transonic and low supersonic speeds is simply a long narrow straight subsonic wing turned at an oblique angle to the flight direction. This theory has been verified by tests at Mach numbers from .6 to 1.4 in supersonic wind tunnel and by comparative studies of transonic transport designs.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 867-883
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  • 30
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    In:  CASI
    Publication Date: 2010-11-08
    Description: Recent theoretical and experimental work in supersonic aerodynamics is reviewed with its practical application in mind. Several arrangements of supporting surfaces and bodies are discussed and in some cases comparisons of theory and experiment are made. Finally, certain phenomena connected with lift and drag in a rarefied medium are considered briefly.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 625-644
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  • 31
    Publication Date: 2010-11-08
    Description: A method is reported for determining mathematically the combined disturbance field, and in certain cases the minimum drag, of wings at supersonic speeds. The simplest analytic example is provided by the wing of elliptic planform, which achieves its minimum drag when the lift is distributed uniformly over the surface. With a symmetrical distribution of thickness, the requirement of minimum drag for a given total volume is found to lead to profiles of constant curvature.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 567-578
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  • 32
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    In:  CASI
    Publication Date: 2010-11-08
    Description: The assumptions of the thin airfoil theory are found to provide certain necessary conditions for the minimum drag of airfoils having a given total lift, a given maximum thickness, or a given volume. The conditions are applicable to steady or unsteady motions and to subsonic or supersonic speeds without restriction on the planform. The computation of drag and the statement of the conditions for minimum drag depend on the consideration of a combined flow field, which is obtained by superimposing the disturbance velocities in forward and reversed motions. If the planform of the airfoil and its total lift are given, it is found that, for minimum drag, the lift must be distributed in such a way that the downwash in the combined field is constant over the entire planform. If the planform is given and the thickness of the airfoil is required to contain a specified volume, then the thickness must be distributed over the planform in such a way that the pressure gradient of the combined field in the direction of flight is constant at all points of the wing.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 557-565
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  • 33
    Publication Date: 2010-11-08
    Description: The application of mathematical advances made in electricity and other branches to problems of airplane dynamics is demonstrated. The Heaviside-Bromwich methods of solution of linear differential equations are described and it is shown how these methods avoid the consideration of boundary conditions and of particular or complementary integrals. It is pointed out that if the solution of the differential equation is obtained for the case of a unit disturbance, the effect of varying disturbances may be found therefrom by Carson's theorem. A graphical solution of Carson's integral for irregular disturbances is given. The procedure of obtaining unit solutions of the equations is then taken up and the analogy between Heaviside's symbolic series solution and a physical procedure of approximation is shown. It is suggested that a fictitious impulsive disturbance be used in the treatment of initial motions.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 21-29
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  • 34
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    In:  CASI
    Publication Date: 2010-11-08
    Description: In linearized flow theory, certain very interesting extremal properties of wings can be derived under rather broad conditions without the use of a complicated mathematical apparatus. The present chapter reviews certain results of this theory and indicates some rather obvious extensions to incorporate various auxiliary conditions. Several examples illustrating the relation between the geometrical features of the wing and the lift distribution for minimum drag are given.
    Keywords: AERODYNAMICS
    Type: NASA. Ames Res. Center Collected Works of Robert T. Jones; p 645-656
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  • 35
    Publication Date: 2010-11-08
    Description: The items discussed are: (1) a recently proposed correction formula for the effect of compressibility in two dimensional subsonic flow; (2) the equivalence rule and the area rule for transonic speeds; (3) reciprocal relations in linearized wing theory; and (4) some general results connected with the problem of minimum wave resistance. The paper concludes with an example showing indentation of the fuselage to obtain favorable interference with the wing at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 601-608
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  • 36
    Publication Date: 2010-11-08
    Description: In the wing section theory the magnitude of the circulation, and hence of the lift, is determined by the velocity that would be induced near the trailing edge of the section in a non-lifting potential flow. In three dimensional flow the problem is complicated by the presence of the wake and no simple basic solution has been found. Treatment of the problem of a wing of finite span is reported on the basis of the two dimensional theory, corrected for the effect of the wake.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 245-249
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  • 37
    Publication Date: 2010-11-08
    Description: In theory, antisymmetric arrangements of wings and bodies can have smaller wave drag than corresponding mirror-symmetric arrangements. Thus, a long narrow oblique wing which presents the same aspect for two opposite directions of flight is potentially more efficient than corresponding (i.e., structurally equivalent) swept wing. The single continuous wing panel also adapts itself more readily to varying angles of obliquity, and hence, to varying flight speeds. Previous work on the aerodynamics and flight stability of oblique wing combinations is reviewed and a possible mode of application to transport aircraft operating at moderate supersonic speeds is suggested.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 657-664
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  • 38
    Publication Date: 2010-11-08
    Description: It is shown that the drag of any semi-infinite airfoil section in purely subsonic inviscid flow follows precisely the Prandtl-Glauert compressibility rule. The result for the parabola has application to leading edge corrections in thin airfoil theory.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 619-623
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  • 39
    Publication Date: 2010-11-08
    Description: Comparisons of wing-body combinations may not disclose the full effect of a loss in aerodynamic efficiency. If the thrust needs to be increased at a given altitude then more or larger engines will have to be used and the possibility of concealing them becomes less. In this process the lift drag ratio of the complete airplane may become still more unfavorable than indicated by the comparison. Primarily aerodynamic and structural considerations point toward the development of turbojet engines specifically adapted to operation in an atmosphere of one tenth normal density. In addition to the numerous other technological problems associated with operation at these high altitudes, the problems of safe descent and effective limitation to low speeds at low altitudes seem important.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 579-592
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  • 40
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    In:  CASI
    Publication Date: 2010-11-08
    Description: If the thin airfoil theory is applied to an airfoil having a rounded leading edge, a certain error will arise in the determination of the pressure distribution around the nose. It is shown that the evaluation of the drag of such a blunt nosed airfoil by the thin airfoil theory requires the addition of a leading edge force, analogous to the leading edge thrust of the lifting airfoil. The method of calculation is illustrated by application to: (1) The Joukowski airfoil in subsonic flow; and (2) the thin elliptic cone in supersonic flow. A general formula for the edge force is provided which is applicable to a variety of wing forms.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 533-538
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  • 41
    Publication Date: 2010-11-08
    Description: Some of the recent advances in the theory of thin airfoils are presented with particular reference to extensions of the theory to three dimensional flows and to supersonic speeds. The problem discussed herein is the calculation of the small disturbance velocities u, v, and w in the external field produced by the flight velocity V of the airfoil.
    Keywords: AERODYNAMICS
    Type: Collected Works of Robert T. Jones; p 483-497
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  • 42
    Publication Date: 2006-01-16
    Description: Results are presented for tests made of the full scale model of the airplane in the NACA full scale tunnel. These tests were planned so as to cover as completely as possible the lateral flying quality requirements for pursuit-type airplanes contracted for by the United States Army Air Forces.
    Keywords: AERODYNAMICS
    Type: Collected Works of Charles J. Donlan; 23 p
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  • 43
    Publication Date: 2011-10-14
    Description: An account is given of a detailed experimental investigation of three dimensional boundary layer separation in supersonic flow. In investigating three dimensional effects on supersonic separation, models were chosen which exhibited departures from two dimensional flow in the simplest way. The plane compression corner was replaced by a plate attached to a swept back wedge formed by two obliquely intersecting planes. Maintaining a constant tunnel Mach number of 2.5, surface pressure measurements were made on these models at static orifices spaced along the centerline and along three parallel lines. The flow parameters in the boundary layer and separated regions adjacent to the model surface were measured by traversing hot wire and pitot probes. The traverses were taken across the boundary layer and reversed flow regions in a direction normal to the body surface; they were made in several vertical planes, including the plane of symmetry.
    Keywords: AERODYNAMICS
    Type: AGARD Flow Separation; 13 p
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  • 44
    Publication Date: 2011-08-17
    Description: The steady-state Navier-Stokes equations are solved for hypersonic flow about blunt axisymmetric bodies. The equations of motion are solved by successive approximations using an implicit finite-difference scheme. The results are compared with viscous shock-layer theory, experimental data, and time-dependent solutions of the Navier-Stokes equations. It is demonstrated that viscous shock-layer theory is sufficiently accurate for the range of flight conditions normally encountered by entry vehicles.
    Keywords: AERODYNAMICS
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  • 45
    Publication Date: 2011-08-17
    Description: A portable boundary-layer meteorological data-acquisition and analysis system is described which employs a small tethered balloon and a programmable calculator. The system is capable of measuring pressure, wet- and dry-bulb temperature, wind speed, and temperature fluctuations as a function of height and time. Other quantities, which can be calculated in terms of these, can also be made available in real time. All quantities, measured and calculated, can be printed, plotted, and stored on magnetic tape in the field during the data-acquisition phase of an experiment.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Boundary-Layer Meteorology; 10; Aug. 197
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  • 46
    Publication Date: 2011-08-17
    Description: A color photograph of the peculiar elliptical galaxy NGC 5128 (Centaurus A) has been reconstructed from three Kodak 103a emulsion type photographs by projecting positives of the three B&W plates through appropriate filters onto a conventional color film. The resulting photograph shows color balance and latitude characteristics superior to color photographs of similar astronomical objects made with commercially available conventional color film. Similar results have been obtained for color reconstructed photographs of the Large and Small Magellanic Clouds. These and other results suggest that these projection-reconstruction techniques can be used to obtain high-quality color photographs of astronomical objects which overcome many of the problems associated with the use of conventional color film for the long exposures required in astronomy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Photographic Engineering; 2; Spring 1
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  • 47
    Publication Date: 2011-08-17
    Description: The paper reports on results of heat-transfer tests conducted on a 1/29-scale model of the X-24C-12I hypersonic research aircraft configuration in a Mach 6 tunnel at a Reynolds number of thirteen million using the phase-change heat transfer technique. Sequences of phase-change heat transfer pattern photographs are presented showing windward side and leeward side heating processes. Theoretical predictions of dimensionless heat transfer coefficients along a data line on lower fuselage and on fuselage side bracket the experimental values. A turbulent heating theory gives good agreement with data when shifted to a new virtual origin.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 13; Dec. 197
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  • 48
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    In:  Other Sources
    Publication Date: 2011-08-17
    Description: The report concerns the measurement of friction coefficients of a typical perforated acoustic liner installed in the side of a wind tunnel. The results are compared with measured friction coefficients of a smooth hard wall for the same mean flow velocities in a wind tunnel. At a velocity of 61 m/sec, an increase in the local skin coefficient of only a few percent was observed, but at the highest velocity of 213 m/sec an increase of about 20% was obtained. This velocity is a realistic velocity for turbo-machinery components utilizing such liners, so a loss in performance is to be expected. Some tests were also performed to see if changes in the mean boundary layer induced by imposed noise would result in friction increase, but only at low velocity levels was such an increase in friction noted.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; Nov. 197
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  • 49
    Publication Date: 2011-08-17
    Description: Supersonic flow past a blunt body is considered, where the flow contains an embedded subsonic region which lies between the shock wave and the body surface and is bounded by sonic lines from the body to the shock. A numerical approach is taken, which uses a basic finite difference scheme that solves the unsteady fluid dynamic equations in integral form. The unsteady equations are everywhere hyperbolic in time so no distinction need be made between subsonic and supersonic regions. Solutions to the mixed elliptic and hyperbolic steady flow equations are approached asymptotically in time. The method is illustrated for two-dimensional flows.
    Keywords: AERODYNAMICS
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  • 50
    Publication Date: 2011-08-16
    Description: The versatility is demonstrated of the 41 cm. Tortugas reflector's photoelectric system through observations of V566 Oph and R CrB with four associated AAVSO comparison stars. These observations were made between May and October, 1974.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Contrib. of the Observatory of N. Mex. State Univ., Vol. 1, No. 4; p 154-158
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  • 51
    Publication Date: 2011-08-17
    Description: An array of large multicrystal NaI(Tl) detectors was constructed and used in a balloon-borne experiment to observe weak transient bursts of cosmic origin. The array had an active area of about 1 sq m and was sensitive to photons above 50 keV. Localized bursts which were observed are attributed to long-lived phosphorescence following large energy deposits by cosmic rays in the crystals.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Nuclear Instruments and Methods; 140; 1976
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  • 52
    Publication Date: 2011-08-17
    Description: An interactive numerical procedure has been developed for supersonic viscous flows (either two-dimensional or axisymmetric configurations). The flow field is divided into two regions: (1) an inner region which is highly viscous and mostly subsonic, and (2) an outer region where the flow is supersonic and in which viscous effects are small, but not negligible. This paper presents a detailed description of: I. Outer Region - numerical solution obtained by applying the method of characteristics to a system of equations which includes viscous and conduction transport terms only normal to the streamlines; II. Inner Region - treated by a system of equations of the boundary-layer type that includes higher order effects, such as longitudinal and transverse curvature and normal pressure gradients (equations are coupled and solved simultaneously in physical coordinates, using an implicit finite-difference scheme); III. Interactive Procedure - in the interaction mode, the two regions are coupled iteratively along a matching line, where the Mach number is of the order of 1.2.
    Keywords: AERODYNAMICS
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  • 53
    Publication Date: 2011-08-17
    Description: Two CCD techniques were discussed for performing an N-point sampled data correlation between an input signal and an electronically programmable reference function. The design and experimental performance of an implementation of the direct time correlator utilizing two analog CCDs and MOS multipliers on a single IC were evaluated. The performance of a CCD implementation of the chirp z transform was described, and the design of a new CCD integrated circuit for performing correlation by multiplication in the frequency domain was presented. This chip provides a discrete Fourier transform (DFT) or inverse DFT, multipliers, and complete support circuitry for the CCD CZT. The two correlation techniques are compared.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; 6 p
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  • 54
    Publication Date: 2011-08-17
    Description: The maturity of self-scanned, solid-state, multielement photosensors makes the realization of "real time" reconnaissance photography viable and practical. A system built around these sensors which can be constructed to satisfy the requirements of the tactical reconnaissance scenario is described. The concept chosen is the push broom strip camera system -- RECON 6 -- which represents the least complex and most economical approach for an electronic camera capable of providing a high level of performance over a 140 deg wide, continuous swath at altitudes from 200 to 3,000 feet and at minimum loss in resolution at higher altitudes.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; p 129-134
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  • 55
    Publication Date: 2011-08-17
    Description: A commercially available 1728 element shallow bulk channel CCD line array was clocked at output data rates up to 30 MHz. Temporal noise was near 200 electrons and was largely independent of clock rate. Charge transfer efficiency was in excess of 0.9999 at 30 MHz. Utilization is feasible for visual simulation and aerial mapping.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; p 72-82
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  • 56
    Publication Date: 2011-08-17
    Description: High performance CCD imagers with 800 x 50 resolution elements were fabricated using a coplanar, double polysilicon, electrode system. The imager was developed as a prototype to demonstrate the feasibility of an 800 x 800 array for application to deep space photography where data rates of 10K to the 2nd power and operating temperatures of -40 C are required. The performance is discussed and comparisons made to the existing 400 x 400 imager.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; 3 p
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  • 57
    Publication Date: 2011-08-16
    Description: An improved technique has been developed for studies of the shear viscosity of fluids. It utilizes an acoustic resonator as a four-terminal electrical device; the resonator's amplitude response may be determined directly and simply related to the fluid's viscosity. The use of this technique is discussed briefly and data obtained in several fluids is presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Acoustical Society of America; vol. 60
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  • 58
    Publication Date: 2011-08-16
    Description: A computer program recently developed by South and Brandt (1976) which contained the Murman (1973) conservative finite-difference scheme is easily modified to use the Garabedian and Korn (1971) nonconservative finite difference scheme. This program solves the transonic small disturbance equation for only symmetric flow, but incorporates several iterative solution techniques. Results are presented for the case where the equally spaced computational grid extended to infinity in both the streamwise and normal directions. Streamline shapes are obtained along several grid lines by a streamwise integration of the normal component of the perturbation velocity. Comparison cases are run for a 10% thick parabolic arc airfoil at zero incidence for freestream Mach numbers of 0, 0.70, 0.84, and 0.95. It is shown that the use of a nonconservative finite-difference scheme in transonic flow calculations destroys the global mass balance when shocks are present. This lack of mass balance may prove to be more crucial in the case of an unconfined external flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; Aug. 197
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  • 59
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    Publication Date: 2011-08-17
    Description: Images on developed photographic emulsions can be significantly intensified by making the image silver radioactive and exposing a second emulsion to this radiation. Because the print, an autoradiograph, reproduces the original with significant increases in density and contrast, the method can be used to enhance underexposed emulsions and to increase the limits of photographic detection. This paper reports a new, practical chemical method for activating the silver, using thiourea labeled with sulfur-35, a process convenient for use in photographic laboratories. Speed increases of 13 and contrast increases of 18 were achieved with Kodak Plus-X film in this initial phase.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; Nov. 197
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  • 60
    Publication Date: 2011-08-17
    Description: Existing techniques for the detection of a moving low light level image by a CCD array have required velocity synchronism between the image and the photogenerated charges. This was necessary to prevent blurring during the long duration of charge integration. A new detection scheme is described which causes the image to be convolved with a clock modulation signal as the photocharges are collected. The charge accumulating from each image point will now be spread over many photoelements due to the absence of velocity synchronism, but the output is not blurred in the usual sense. Instead the charge is distributed through the array in a controlled way so that the image can be reconstructed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; p 139-144
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  • 61
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    Publication Date: 2011-08-17
    Description: Intensified CCDs (ICCDs) were built and operated. These ICCDs were electrostatically and magnetically-focussed image tubes which use CCDs as anodes. The ICCDs detected single photoelectrons, and have electron gain very near that which was predicted. The first single-pixel pulse-height distributions were presented, and the leakage current was shown to increase as a function of photoelectron irradiation. The advantages and disadvantages of front- and rear-illuminated designs were discussed in light of differing applications requirements.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; p 101-105
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  • 62
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    Publication Date: 2011-08-17
    Description: Various techniques were developed which enable the CCD (charge coupled device) imaging array user to obtain optimum performance from the device. A CCD video channel was described, and detector-preamplifier interface requirements were examined. A noise model for the system was discussed at length and laboratory data presented and compared to predicted results.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: JPL Conf. on Charge-Coupled Device Technol. and Appls.; p 83-88
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  • 63
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    Publication Date: 2011-08-16
    Description: The principles of operation of solid state nondispersive spectrometers are reviewed. Si(Li) is shown to be the preferred nondispersive X-ray spectrometer because of its inherent resolution advantages and its adaptability to the constraints and philosophy of the HEAO-B observatory. A schematic diagram is presented of the geometry of the HEAO-B solid state detector assembly as a block diagram of the primary logic mode of the HEAO-B X-ray spectrometer.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 64
    Publication Date: 2011-08-16
    Description: A flow-visualization study has shown that strong Karman vortices develop behind the blunt trailing edge of a plate when the free-stream velocities over both surfaces are equal and that the vortices tend to disappear when the surface velocities are unequal. This observation provides an explanation for the occurence and disappearance of certain discrete tones often found to be present in the noise spectra of coaxial jets. Both the vortex formation and the tones occur at a Strouhal number based on the lip thickness and the average of the external steady-state velocities of about 0.2. Results from theoretical calculations of the vortex formation, based on an inviscid incompressible analysis of the motion of point vortices, were in good agreement with the experimental observations.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 75; June 25
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  • 65
    Publication Date: 2011-08-16
    Description: The rationale for a Water Vapor Radiometer (WVR) as an aid in predicting tropospheric delay correction is presented. Included is a block diagram and a description of the present developmental WVR with the semiautomated operating sequence outlined. A brief summary of field tests at El Monte airport and Pt. Mugu is given.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: The Deep Space Network; p 77-84
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  • 66
    Publication Date: 2011-08-16
    Description: An in situ fracture device for Auger spectroscopy is described. The device is designed to handle small tensile specimens or small double-cantilever beam specimens and is fully instrumented with load and displacement transducers so that quantitative stress-strain measurements can be made directly. Some initial test results for specimens made from 4130 and 1020 steel are presented. Results indicate that impurity segregation at interfaces other than grain boundary may play a significant role in the mechanism of ductile fracture.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 47; Apr. 197
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  • 67
    Publication Date: 2011-08-16
    Description: The factors determining the sensitivity of a real astronomical heterodyne spectrometer are described. The deviation from the ideal heterodyne system for line detection is described in terms of a series of degradation factors. A discussion of degradation due to a low local oscillator power and to line profile detection is presented. Representative values for the degradation factors are given. Even with a total degradation of not less than 30, the heterodyne spectrometer is still found to be a highly sensitive tool in IR astronomy.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 68
    Publication Date: 2011-08-16
    Description: The performance of an upconversion system is examined for observation of astronomical sources in the low to middle IR spectral range. Theoretical values for the performance parameters of an upconversion system for astronomical observations are evaluated in terms of the conversion efficiencies, spectral resolution, field of view minimum detectable source brightness, and source flux. Experimental results of blackbody measurements and molecular absorption-spectrum measurements using a lithium niobate upconverter with an argon-ion laser as the pump are presented. Estimates are given of the expected optimum sensitivity of an upconversion device that may be built with presently available components.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; Apr. 197
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  • 69
    Publication Date: 2011-08-16
    Description: Black body measurements and absorption spectra of methane near 3.3 microns are presented and used as examples in a discussion of upconversion spectrometry for astrophysical application. Factors determining the system conversion efficiency and the minimum detectable flux for a typical system are presented. The spectrometer described uses an Argon-ion laser and a temperature turned LiNbO3 crystal in a CW mode. Satisfactory agreement between measured and calculated performance parameters is obtained. An estimate of the highest performance parameters attainable using current technology is given.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
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  • 70
    Publication Date: 2011-08-16
    Description: The paper examines the heating levels experienced by a probe entering Kliore's (1974) model of Jupiter's atmosphere and compares the results with those of the Jupiter model atmospheres given elsewhere (NASA SP-8069, 1971), with the heating levels of Tauber (1969) and Tauber and Wakefield (1971). The computations are made using a point-mass atmospheric entry trajectory program, i.e., the Allen-Eggers (1958) analysis and simple correlations of heating. Results of heating calculations are compared and discussed. It is found that the warm temperature bulge exists at a level too low in the atmosphere to affect any heating and that the nominal atmosphere fits Kliore's model atmosphere best insofar as heating is concerned. Previous estimates of the heating levels to be expected for a probe entering Jupiter's atmosphere are therefore unaffected by Kliore's postulated atmospheres.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 13; Feb. 197
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  • 71
    Publication Date: 2011-08-16
    Description: Tripping effectiveness of surface roughness on a delta wing shuttle orbiter model at 20 deg angle of attack is compared to that on plane and axisymmetrical bodies with and without longitudinal pressure gradients. The experimental data presented are compared on the basis of effective roughness Reynolds number since this parameter is not sensitive to flow conditions downstream of the roughness. The discussion covers the effective roughness Reynolds number as a function of roughness position Reynolds number, effective size ratio as a function of pressure gradient and distance from vehicle nose, and effect of spanwise roughness position on roughness effectiveness. It is shown that conventional criteria for sizing roughness elements which promote transition in two-dimensional zero-pressure gradient flows are insufficient for high-pressure gradient flows and three-dimensional flows. Roughness much smaller than that given by conventional criteria can cause transition and significantly increase the heating load.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 13; Feb. 197
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  • 72
    Publication Date: 2011-08-16
    Description: A uniformly valid second-order theory is developed for calculating the unsteady incompressible flow that occurs when an airfoil is subjected to a convected sinusoidal gust. Explicit formulas for the airfoil response functions (i.e., fluctuating lift) are given. The theory accounts for the effect of the distortion of the gust by the steady-state potential flow around the airfoil, and this effect is found to have an important influence on the response functions. A number of results relevant to the general theory of the scattering of vorticity waves by solid objects are also presented.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 74; Apr. 22
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  • 73
    Publication Date: 2011-08-16
    Description: A technique is described for the efficient numerical solution of nonlinear partial differential equations by rapid iteration. In particular, a special approach is described for applying the Aitken acceleration formula (a simple Pade approximant) for accelerating the iterative convergence. The method finds the most appropriate successive approximations, which are in a most nearly geometric sequence, for use in the Aitken formula. Simple examples are given to illustrate the use of the method. The method is then applied to the mixed elliptic-hyperbolic problem of steady, inviscid, transonic flow over an airfoil in a subsonic free stream.
    Keywords: AERODYNAMICS
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  • 74
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    Publication Date: 2011-08-16
    Description: Different inlet designs for high angle of attack STOL and VTOL applications were tested in a subsonic wind tunnel. Three removable entry lips having contraction ratios of 1.30, 1.34 and 1.38 were tested with a single diffuser. The internal contour of each entry lip was an ellipse with a major to minor axis of 2.0. Each lip and diffuser assembly was tested to determine its tolerance to angle of attack, first with a conventional centerbody and then with an extended centerbody. Results indicate that a large improvement in separation angle (determined as a function of lip contraction ratio and inlet flow) was obtained for the extended centerbody for all contraction ratios. Improved inlet tolerance to angle of attack was obtained by reducing the adverse pressure gradient downstream of the throat.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 13; Apr. 197
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  • 75
    Publication Date: 2011-08-16
    Description: Experiments were carried out to evaluate the effects of normal velocity gradients on hot wire measurements in a subsonic boundary layer of the same size as the flow investigated by Johnson and Rose (1975). Both hot wire and film anemometers were used to measure the turbulent properties of the boundary layer. A special X-wire probe with one wire vertical and the other at an angle of about 40 deg to the flow was used to demonstrate the gradient effects. The results indicate that major errors are encountered when mean and turbulent velocity gradients exist along the length of hot wire sensors, the problem being more pronounced at high speeds. Although the split film sensor results show a significant improvement over the X-wire sensor, further reduction in the space resolution of sensors by roughly an order of magnitude would appear to be necessary to reduce the error to acceptable values near the wall.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal; 14; Mar. 197
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  • 76
    Publication Date: 2012-05-19
    Description: An experimental program was initiated at Langley Research Center to study the effects of various parameters on the design of laminar proportional beam deflection amplifiers. Matching and staging of amplifiers to obtain high-pressure gain was also studied. Variable parameters were aspect ratio, setback, control length, receiver distance, receiver width, width of center vent, and bias pressure levels. Usable pressure gains from 4 to 19 per stage can now be achieved, and five amplifiers were staged together to yield pressure gains up to 2,000,000.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AGARD Fluidics Technol.; p 209-227
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  • 77
    Publication Date: 2011-08-17
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Reviews of Geophysics and Space Physics; 14; Nov. 197
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  • 78
    Publication Date: 2011-08-16
    Description: Angular responses have been measured for X-ray collimators with half-widths ranging from minutes of arc down to 10 arcsec. In the seconds-of-arc range, diffraction peaks at off-axis angles can masquerade as side lobes of the collimator angular response. Measurements and qualitative physical arguments lead to a rule of thumb for collimator design; namely, the angle of first minimum in the Fraunhofer single-slit diffraction pattern should be less than one-fourth of the collimator geometrical full-width at half-maximum intensity.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 47; Aug. 197
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  • 79
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    Publication Date: 2011-08-16
    Description: The basic data and approach for calibrating photographic plates obtained with the 61 cm telescope at the Tortugas Mountain Station of New Mexico State University are summarized. Since this is the fundamental calibration of planetary data it is of use to all in-house users as well as other individuals who use the data.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Contrib. of the Observatory of N. Mex. State Univ., Vol. 1, No. 4; p 159-163
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  • 80
    Publication Date: 2011-08-16
    Description: Observations over four months are used to evaluate magnitude and color transformations, extinction coefficients, and a gain table for the photoelectric photometer of the 41 cm. reflector at the Tortugas Mountain site. Ways of increasing the efficiency and accuracy of this system are discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Contrib. of the Observatory of N. Mex. State Univ., Vol. 1, No. 4; p 148=153
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  • 81
    Publication Date: 2011-08-16
    Description: A discussion and an evaluation of the degradation in sensitivity are given for a heterodyne spectrometer employing a HgCdTe photodiode mixer and tunable diode lasers. The minimum detectable source brightness is considered as a function of the mixer parameters, transmission coefficient of the beam splitter, and local oscillator emission powers. The degradation in the minimum detectable line source brightness that results from the bandwidth being a fraction of the line width is evaluated and plotted as a function of the wavelength and bandwidth for various temperature to mass ratios. It is shown that the minimum achievable degradation in the sensitivity of a practical astronomical heterodyne spectrometer is about 30. Estimates of SNRs with which IR line emission from astronomical sources of interest may be detected are given.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; Feb. 197
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  • 82
    Publication Date: 2011-08-16
    Description: The general applicability of dynamic theory to the description of the recording and readout characteristics of volume (thick) hologram gratings is indicated. In dynamic theory (as opposed to static theory), the volume nature of the thick holographic grating allows the interference of an incident light beam with its own diffracted beam inside the recording medium. This effect causes the continuous recording of another grating that alters the initial one, producing a resultant grating that is not uniform through the thickness of the recording material and a grating whose writing and reading characteristics may vary dramatically, depending on the recording material and the experimental conditions. A large number of diverse types of writing, reading, and angular-selectivity behavior have been reported. The dynamic theory of thick-hologram writing and reading is shown to predict qualitatively all of these various types of experimental behavior.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Journal of Applied Physics; 47; Jan. 197
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  • 83
    Publication Date: 2011-08-16
    Description: Image quality criteria and image quality predictions are formulated for the multispectral panoramic cameras carried by the Viking Mars landers. Image quality predictions are based on expected camera performance, Mars surface radiance, and lighting and viewing geometry (fields of view, Mars lander shadows, solar day-night alternation), and are needed in diagnosis of camera performance, in arriving at a preflight imaging strategy, and revision of that strategy should the need arise. Landing considerations, camera control instructions, camera control logic, aspects of the imaging process (spectral response, spatial response, sensitivity), and likely problems are discussed. Major concerns include: degradation of camera response by isotope radiation, uncertainties in lighting and viewing geometry and in landing site local topography, contamination of camera window by dust abrasion, and initial errors in assigning camera dynamic ranges (gains and offsets).
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; July 197
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  • 84
    Publication Date: 2011-08-16
    Description: The study presents wind-tunnel measurements of surface static pressures, equilibrium temperatures, and skin friction downstream of tangential slot injection into a thick turbulent hypersonic boundary layer from two modified slot configurations. The data are compared with results obtained for baseline configurations reported by Cary and Hefner (1970, 1972) to determine whether simple modifications to the slot configuration can produce improved cooling effectiveness and skin friction reduction. The baseline slot configurations are simply modified by thickening the slot lip and by elevating the location of the slot exit above the flat plate. Although the results indicate that simple modifications of the baseline slot configurations can enhance the skin friction reductions obtained with tangential slot injection, slot base drag estimates show that neither of the modifications will lessen the impact of the systems penalties for collecting, ducting, and injecting the slot air.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; June 197
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  • 85
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    Publication Date: 2011-08-16
    Description: A method is described for measuring the conductivity of materials without having to make electrical contact with the material. Currents which are magnetically induced in the conducting sample are measured by means of the magnetic fields they produce. Although induction techniques have been used in the past for this type of measurement, the configuration presented here makes it possible to perform absolute measurements of resistivity over a wide range of values for relatively small samples. The theory of the technique, the results of measurements made with it, and a comparison of the technique with other methods are presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments; 47; June 197
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  • 86
    Publication Date: 2011-08-16
    Description: Carbon foils were positioned at roughly 10 deg to the conventional perpendicular position so that the spectrometer would view the beam on emergence from the foil, with no radiation shielded by a bowed or wrinkled foil or by the foil holder. Extraneous peaks due to reflected radiation were detected in the spectrum obtained with the tilted foil. A large satellite appears longward of the spectral line and is attributed to Doppler-shifted radiation reflected from the foil surface. Special tests arranged to validate the origin of the satellites are described. The relative intensity of the reflected radiation compared with the direct radiation observed is at variance with the relative intensities reported for longer wavelengths. The reasons for this, possible effects of spectrometer geometry, and applications in the investigation or generation of polarization remain to be investigated
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; Aug. 197
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  • 87
    Publication Date: 2011-08-16
    Description: Turbulent intensity and Reynolds shear stress measurements are presented for two nonadiabatic hypersonic shock-wave boundary-layer interaction flows, one with and one without separation. These measurements were obtained using a new hot-wire probe specially designed for heated flows. Comparison of the separated and attached flows shows a significant increase above equilibrium values in the turbulent intensity and shear stress downstream of the interaction region for the attached case, while for the separated case, the turbulent fluxes remain close to equilibrium values. This effect results in substantial differences in turbulence lifetime for the two flows. We propose that these differences are due to a coupling between the turbulent energy and separation bubble unsteadiness, a hypothesis supported by the statistical properties of the turbulent fluctuations.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; May 1976
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  • 88
    Publication Date: 2011-08-16
    Description: A method for determining the refractive index profile of thick phase gratings in linear electrooptic crystals is presented. This method also determines the effective photovoltaic electric field and the relative contributions of diffusion and drift during hologram recording. The method requires only a knowledge of the modulation ratio during hologram recording and the fundamental and the higher-order diffraction efficiencies of the grating. As an illustration of the method, the refractive index profile, the effective photovoltaic field, and the relative contributions of diffusion and drift are determined from experimental measurements for a lithium niobate holographic grating.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 15; Aug. 197
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  • 89
    Publication Date: 2011-08-16
    Description: Severe flow separation in the 15:1 area-ratio, 38 deg total angle conical diffuser preceding the settling-chamber of an intermittent blowdown wind tunnel was eliminated by the use of a novel radial-splitter arrangement. As a consequence, the operating life of settling-chamber screens was greatly extended and test-section flow steadiness improved, with no penalty in the tunnel running time.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 13; July 197
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  • 90
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    Publication Date: 2011-08-16
    Description: Oversampling is defined as sampling with a device whose characteristic width is greater than the interval between samples. This paper shows why oversampling should be avoided and discusses the limitations in data processing if circumstances dictate that oversampling cannot be circumvented. Principally, oversampling should not be used to provide interpolating data points. Rather, the time spent oversampling should be used to obtain more signal with less relative error, and the Sampling Theorem should be employed to provide any desired interpolated values. The concepts are applicable to single-element and multielement detectors.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Astronomical Journal; 81; Apr. 197
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  • 91
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    In:  Other Sources
    Publication Date: 2011-08-17
    Description: The use and limitations on using computational aerodynamics in approximating inviscid linear, inviscid nonlinear, vicous time averaged, and viscous time dependent flow past airfoils, wings, and aircraft is reviewed. The current status of two- and three-dimensional time averaged Navier-Stokes equation is discussed and possible applications for the 1980 and 1985 to 1990 period is projected for three-dimensional applications.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dyn. Computational Fluid Dyn., Vol. 2; 36 p
    Format: text
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  • 92
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    In:  Other Sources
    Publication Date: 2011-08-17
    Description: Although the development of a finite difference relaxation procedure to solve the steady form of equations of motion gave birth to the study of computational transonic aerodynamics and considerable progress has been made using the small disturbance theory, no general analytical solution method yet exists for transonic flows that include three dimensional unsteady, and viscous effects. Two techniques are described which are useful in computational transonic aerodynamics applications. The finite volume method simplifies the application of boundary conditions without introducing the constriction associated with small disturbance theory. Governing equations are solved in a Cartesian coordinate system using a body-oriented and shock-oriented mesh network. Only the volume and surface normal directions of the volume elements must be known. The other method, configuration design by numerical optimization, can be used by aircraft designers to develop configurations that satisfy specific geometric performance constraints. Two examples of airfoil design by numerical optimization are presented.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dyn. Computational Fluid Dyn., Vol. 1; 122 p
    Format: text
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  • 93
    Publication Date: 2011-08-17
    Description: Calculation procedures for non-reacting compressible two- and three-dimensional turbulent boundary layers were reviewed. Integral, transformation and correlation methods, as well as finite difference solutions of the complete boundary layer equations summarized. Alternative numerical solution procedures were examined, and both mean field and mean turbulence field closure models were considered. Physics and related calculation problems peculiar to compressible turbulent boundary layers are described. A catalog of available solution procedures of the finite difference, finite element, and method of weighted residuals genre is included. Influence of compressibility, low Reynolds number, wall blowing, and pressure gradient upon mean field closure constants are reported.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dyn. Compressible Turbulent Boundary Layers, Vol. 2; 124 p
    Format: text
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  • 94
    Publication Date: 2016-06-07
    Description: Flow turning parameters, static pressures, surface temperatures, surface fluctuating pressures and acceleration levels were measured in the environment of a full-scale upper surface blowing (USB) propulsive lift test configuration. The test components included a flightworthy CF6-50D engine, nacelle, and USB flap assembly utilized in conjunction with ground verification testing of the USAF YC-14 Advanced Medium STOL Transport propulsion system. Results, based on a preliminary analysis of the data, generally show reasonable agreement with predicted levels based on model data. However, additional detailed analysis is required to confirm the preliminary evaluation, to help delineate certain discrepancies with model data, and to establish a basis for future flight test comparisons.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 479-496
    Format: application/pdf
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  • 95
    Publication Date: 2016-06-07
    Description: The objectives of the NASA Advanced Medium STOL Transport Experiments Program are discussed and several of the NASA experiments currently implemented and conducted on the YC-14 and YC-15 prototype aircraft are described. Emphasis is placed on experiments related to powered lift aerodynamics and acoustics.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 465-478
    Format: application/pdf
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  • 96
    Publication Date: 2016-06-07
    Description: The statistical properties of tangential flows over surfaces were investigated by two techniques. In one, a laser-Doppler velocimeter was used in a smoke-laden jet to measure one-point statistical properties, including mean velocities, turbulent intensities, intermittencies, autocorrelations, and power spectral densities. In the other technique, free stream and surface pressure probes connected to 1/8 inch microphones were used to obtain single point rms and 1/3 octave pressures, as well as two point cross correlations, the latter being converted to auto spectra, amplitude ratios, phase lags, and coherences. The results of these studies support the vortex model of jets, give some insights into the effects of surface impingement, and confirm that jet diameter and velocity are the scaling parameters for circular jets, while Reynolds number is relatively unimportant.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 445-463
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  • 97
    Publication Date: 2016-06-07
    Description: Static aerodynamic loads measurements from wind tunnel tests of a full-scale upper surface blown jet flap configuration are presented. The measured loads are compared with calculations using a method for predicting longitudinal aerodynamic characteristics of upper surface blown jet flap configurations.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 415-428
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  • 98
    Publication Date: 2016-06-07
    Description: Data presented from large-scale model tests with jet engines having thrusts of 9 kN (2000 lb) and 36 kN (8000 lb) include acoustic loads for an externally blown wing and flap induced by a TF34 jet engine, an upper surface blown (USB) aircraft model in a wind tunnel, and two USB models in static tests. Comparisons of these results with results from acoustic loads studies on configurations of other sizes are made and the implications of these results on interior noise and acoustic fatigue are discussed.
    Keywords: AERODYNAMICS
    Type: Powered-Lift Aerodyn. and Acoustics; p 429-443
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  • 99
    Publication Date: 2016-06-07
    Description: As part of the Quiet Clean Short-Haul Experimental Engine Program, model tests were conducted to determine the effects of thrust reverser geometric parameters on noise and reverse thrust. The acoustic tests used a 1/6 scale model thrust reverser while the aerodynamic performance tests used a 1/12 scale model reverser. Parameters which were varied in both tests include blocker spacing, blocker height, lip angle, and lip length. The impact of these parameters on peak sideline noise and reverse thrust performance is discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 403-414
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  • 100
    Publication Date: 2016-06-07
    Description: Tests conducted to develop the technology necessary to meet the unique reverse-thrust performance requirements of a variable pitch fan propulsion system are discussed. The losses and distortion associated with the air entering the fan and core compressor from the rear of the engine, the direction of fan blade pitch rotation for best reverse-thrust aeroacoustic performance, and engine response and operating characteristics during forward- to reverse-thrust transients are among the factors studied. The test results of several scale fan models as well as a full-size variable pitch fan engine are summarized. Results show the following: a flared exhaust nozzle makes a good reverse-thrust inlet; acceptable core inlet duct recovery and distortion levels in reverse flow were demonstrated; adequate thrust levels were achieved; forward- to reverse-thrust response time achieved was better than the goal; thrust and noise levels strongly favor reverse through feather pitch; and finally, flight-type inlets make the establishment of reverse flow more difficult.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 387-402
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