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  • 1980-1984  (7)
  • 1970-1974  (5)
  • 1
    Electronic Resource
    Electronic Resource
    The fiber saturation point of various morphological subdivisions of Douglas-fir and aspen wood (1972)
    Springer
    Wood science and technology 6 (1972), S. 81-84 
    Details
    ISSN: 1432-5225
    Source: Springer Online Journal Archives 1860-2000
    Topics: Agriculture, Forestry, Horticulture, Fishery, Domestic Science, Nutrition , Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Summary In both Douglas-fir and aspen wood, the fiber saturation point of early wood is greater than that of late wood, solvent extraction lowers the fiber saturation point, and the fiber saturation point for reaction wood is less than that for whole wood.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00350822
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    Paper (German National Licenses)
    Fulltext
  • 2
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    NASA low-speed centrifugal compressor for fundamental research (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new centrifugal compressor facility being built by the NASA Lewis Research Center is described; its purpose is to obtain 'benchmark' experimental data for internal flow code verification and modeling. The facility will be heavily instrumented with standard pressure and temperature probes and have provisions for flow visualization and laser Doppler velocimetry. The facility will accommodate rotational speeds to 2400 rpm and will be rated at pressures to 1.25 atm. The initial compressor stage for testing is geometrically and dynamically representative of modern high-performance stages with the exception of Mach number levels. Design exit tip speed for the initial stage is 500 ft/sec with a pressure ratio of 1.17. The rotor exit backsweep is 55 deg from radial. The facility is expected to be operational in the first half of 1985.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 83-1351
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Improved method for calculating transonic velocities on blade-to-blade stream surfaces of a turbomachine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method was developed to improve the accuracy of an existing computer program used to calculate transonic velocities on a blade-to-blade surface of a turbomachine. The method eliminates problems encountered in obtaining solutions with the velocity gradient equation when large gradients in velocity occur through the blade row. With the improved method, results indicate that the transonic solution can be obtained by scaling the velocities obtained at the reduced mass flow rate where all velocities are subsonic thereby eliminating the need for a solution of the velocity gradient equation. Solutions obtained with the scaling method on a two dimensional compressor cascade and an axial turbine stator show good agreement with experimental data. The results obtained for the stationary blade rows and comparison of analytical results obtained with and without the present method suggest that the method will yield an improved solution for centrifugal compressor impellers.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1772 , E-128
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Power conversion in electrical networks (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aspects of dc to dc conversion were studied in terms of a class of switching voltage regulators from a stability viewpoint. Background concepts of nonlinear system theory were considered, including the problem of obtaining suitable realizations for a class of positive operators. It is shown that the state evolution equations for a power conversion network are in general of bilinear form, and that the theory of lie groups and lie algebras is useful in analyzing such systems. The feedback stabilization of a class of bilinear systems whose state space is a manifold is also discussed.
    Keywords: ELECTRONIC EQUIPMENT
    Type: NASA-CR-120830
    Format: application/pdf
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  • 5
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    Input generator for Denton 3-dimensional turbomachine-blade-row analysis code (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A users manual is presented for a computer program that prepares the bulk of the input data set required for the Denton three dimensional turbomachine blade row analysis code. The Denton input is generated from a minimum of geometry and flow variable information by using cubic spline curve fitting procedures. The features of the program are discussed. The input is described and special instructions are included to assist in its preparation. Sample input and output are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83324 , E-1565 , NAS 1.15:83324
    Format: application/pdf
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  • 6
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    Switched electrical networks and bilinear equations (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation is conducted concerning the state equations which arise in the description of power processing systems. Attention is given to the role played by Lie groups and Lie algebras in the characterization of the dynamical features of the systems. The bilinear equations used for the representation of the network characteristics are discussed along with the nature of the solutions for the equations. The application of the described approaches is illustrated with the aid of a number of network examples.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Annual Allerton Conference on Circuit and System Theory; Oct 03, 1973 - Oct 05, 1973; Monticello, IL
    Format: text
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  • 7
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    Application of system theory to power processing problems (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The work in power processing is reported. Input-output models, and Lie groups in control theory are discussed along with the methods of analysis for time invariant electrical networks.
    Keywords: MATHEMATICAL AND COMPUTER SCIENCES (GENERAL)
    Type: NASA-CR-134708
    Format: application/pdf
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  • 8
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    NASA Low-Speed Centrifugal Compressor for Fundamental Research (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A centrifugal compressor facility being built by the NASA Lewis Research Center is described; its purpose is to obtain benchmark experimental data for internal flow code verification and modeling. The facility will be heavily instrumented with standard pressure and temperature probes and have provisions for flow visualization and laser Doppler velocimetry. The facility will accommodate rotational speeds to 2400 rpm and will be rated at pressures to 1.25 atm. The initial compressor stage for testing is geometrically and dynamically representative of modern high-performance stages with the exception of Mach number levels. Design exit tip speed for the initial stage is 500 ft/sec with a pressure ratio of 1.17. The rotor exit backsweep is 55 deg from radial.
    Keywords: AERODYNAMICS
    Type: NASA-TM-83398 , E-1675 , NAS 1.15:83398 , Joint Propulsion Conf. and Tech. Display; Jun 27, 1983 - Jun 29, 1983; Seattle
    Format: application/pdf
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  • 9
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    Investigation of the three-dimensional flow field within a transonic fan rotor - Experiment and analysis (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation of the three-dimensional flow field through a low aspect ratio, transonic, axial flow fan rotor has been conducted, using an advanced laser anemometer (LA) system. Laser velocimeter measurements of the rotor flow field at the design operating speed and over a range of throughflow conditions are compared to analytical solutions. The numerical technique used herein yields the solution to the full, three-dimensional, unsteady Euler equations using an explicit time-marching, finite volume approach. The numerical analysis, when coupled with a simplified boundary layer calculation, generally yields good agreement with the experimental data. The test rotor has an aspect ratio of 1.56, a design total pressure ratio of 1.629 and a tip relative Mach number of 1.38. The high spatial resolution of the LA data matrix (9 radial x 30 axial x 50 blade-to-blade) permits details of the transonic flow field such as shock location, turning distribution, and blade loading levels to be investigated and compared to analytical results.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 84-GT-200
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3 (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A conical-flow compressor stage with a large radius change through the rotor was tested at three values of rotor tip clearance. The stage had a tandem rotor and a tandem stator. Peak efficiency at design speed was 0.774 at a pressure ratio of 2.613. The rotor was tested without the stator, and detailed survey data were obtained for each rotor blade row. Overall peak rotor efficiency was 0.871 at a pressure ratio of 2.952.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2034 , E-369 , NAS 1.60:2034 , AVRADCOM-TR-81-C-5
    Format: application/pdf
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