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  • Other Sources  (7)
  • 1980-1984  (7)
  • 1965-1969
  • 1981  (7)
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  • 1980-1984  (7)
  • 1965-1969
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  • 1
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    Frequency and timing system for the consolidated DSN and STDN tracking network (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The consolidation on the existing Deep Space Network (DSN) and colocated Goddard Spaceflight Tracking and Data Network (STDN) stations into a multiple antenna array is discussed. Each site includes a signal processing center (SPC) centered in an array of four or five antennas each located within approximately 300 to 800 meters of the SPC. A central frequency and timing system (FTS) located in the SPC contains reference frequency, timing and time code generation, and distribution equipment for both the SPC and each antenna with its associated front end antenna control building. The reference frequency distribution and clock equipment are driven by a hydrogen maser as the prime frequency standard with cesium beam frequency standard as the secondary.
    Keywords: COMMUNICATIONS AND RADAR
    Type: NASA. Goddard Space Flight Center Proc. of the 12th Ann. Precise Time and Time Interval Appl. and Planning Meeting; p 591-614
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Atmospheric environment for space shuttle (STS-1) launch (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Atmospheric conditions near space shuttle STS-1 launch time on April, 12, 1981, at Kennedy Space Center, Florida, are reported. Values of ambient pressure, temperature, moisture, ground winds, visual observations (cloud), and winds aloft are included. The sequence of prelaunch Jimsphere measured vertical wind profiles is presented. Also presented are the wind and thermodynamic parameters measured at the surface and aloft in the SRB descent/impact ocean area. Final meteorological data tapes for STS-1 vehicle ascent, and SRB descent have been constructed which consist of wind and thermodynamic parameters versus altitude.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA-TM-82436
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Atmospheric environment for Space Shuttle (STS-2) launch (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Selected atmospheric conditions observed near Space Shuttle STS-2 launch time on November 12, 1981, or Kennedy Space Center, Florida are summarized. Values of ambient pressure, temperature, moisture, ground winds, visual observations (cloud), and winds aloft are included. The sequence of prelaunch Jimsphere measured vertical wind profiles is given in this report. Wind and thermodynamic parameters measured at the surface and aloft in the SRB descent/impact ocean area are also presented. Final meteorological tapes, which consist of wind and thermodynamic parameters versus altitude, for STS-2 vehicle ascent and SRB descent have been constructed. The STS-2 ascent meteorological data tape was constructed.
    Keywords: METEOROLOGY AND CLIMATOLOGY
    Type: NASA-TM-82463 , NAS 1.15:82463
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Jet impingement heat transfer enhancement for the GPU-3 Stirling engine (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer model of the combustion-gas-side heat transfer was developed to predict the effects of a jet impingement system and the possible range of improvements available. Using low temperature (315 C (600 F)) pretest data in an updated model, a high temperature silicon carbide jet impingement heat transfer system was designed and fabricated. The system model predicted that at the theoretical maximum limit, jet impingement enhanced heat transfer can: (1) reduce the flame temperature by 275 C (500 F); (2) reduce the exhaust temperature by 110 C (200 F); and (3) increase the overall heat into the working fluid by 10%, all for an increase in required pumping power of less than 0.5% of the engine power output. Initial tests on the GPU-3 Stirling engine at NASA-Lewis demonstrated that the jet impingement system increased the engine output power and efficiency by 5% - 8% with no measurable increase in pumping power. The overall heat transfer coefficient was increased by 65% for the maximum power point of the tests.
    Keywords: URBAN TECHNOLOGY AND TRANSPORTATION
    Type: NASA-TM-82727 , DOE/NASA/51040-33
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Transonic Flow Past a Symmetrical Airfoil at High Angle of Attack (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results of an experimental investigation of shock-induced stall and leading-edge stall on a 64A010 airfoil section are presented. Advanced nonintrusive techniques - laser velocimetry and holographic interferometry - were used in characterizing the inviscid and viscous flow regions. The measurements include Mach contours of the inviscid now regions, and mean velocity, flow direction, and Reynolds shear stress profiles in the separated regions. The experimental observations of this study are relevant to efforts to improve surface-pressure prediction methods for airfoils at or near stall.
    Keywords: Aerodynamics
    Type: NASA/TM-81-207541 , NAS 1.15:207541 , AIAA Paper 79-1500R , Journal of Aircraft; 18; 1; 7-14|Fluid and Plasma Dynamics Conference; Jul 23, 1979 - Jul 24, 1979; Williamsburg, VA; United States
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    NASA TECHNICAL REPORTS
  • 6
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    Measurements of the boundary layer and near wake of a supercritical airfoil at cruise conditions (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The flow behavior within the upper-surface boundary layer and near wake of a supercritical airfoil operating at cruise conditions is discussed. Experimental results obtained from wind-tunnel tests are presented which provide a more detailed description of the flow in these regions than was previously available. Mean streamwise velocity profiles measured by pitot-pressure-probe and laser-velocimeter techniques were found to be in excellent agreement. Other mean-flow properties obtained by the laser-velocimeter technique were the local flow angles in the viscous layers and the static pressures at the edges of the boundary layer and wake. The data set also includes measurements of the turbulence intensity and turbulent Reynolds-stress distributions as obtained by the laser-velocimeter technique. To assess the effects of the shock wave, a less extensive set of measurements was realized at a subcritical test condition. The two test conditions (Mach number at free-stream conditions = 0.72, airfoil section lift coefficient = 0.76 and Mach number of free-stream conditions = 0.5, airfoil section lift coefficient = 0.75) provide a good test for state-of-the-art prediction methods because the upper-surface-boundary layer is separated just upstream of the trailing edge in both cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-1242 , Fluid and Plasma Dynamics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Laser velocimetry applied to transonic flow past airfoils (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Measurements of turbulent Reynolds stresses and mean velocities obtained by laser velocimetry for cases of transonic shock-induced separation are presented. These results are compared with solutions of the Reynolds-averaged time-independent compressible Navier-Stokes equations. Insufficient agreement between predictions and experimental results is attributed to the deficiencies in the models for the turbulence Reynolds stresses.
    Keywords: AERODYNAMICS
    Type: Symposium on Numerical and Physical Aspects of Aerodynamic Flows; Jan 19, 1981 - Jan 21, 1981; Long Beach, CA
    Format: text
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    NASA TECHNICAL REPORTS
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