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  • Weitere Quellen  (4)
  • AERODYNAMICS
  • Animals
  • General Chemistry
  • Instrumentation and Photography
  • Spacecraft Design, Testing and Performance
  • Technology Utilization and Surface Transportation
  • 2005-2009
  • 1955-1959
  • 1950-1954  (3)
  • 1930-1934
  • 1925-1929  (1)
  • 1950  (3)
  • 1926  (1)
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  • 2005-2009
  • 1955-1959
  • 1950-1954  (3)
  • 1930-1934
  • 1925-1929  (1)
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  • 1
    facet.materialart.
    Unbekannt
    Lattice arrangements for rapid convergence (1926)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: A simple, systematic, optimized vortex-lattice approach is developed for application to lifting-surface problems. It affords a significant reduction in computational costs when compared to current methods. Extensive numerical experiments have been carried out on a wide variety of configurations, including wings with camber and single or multiple flaps, as well as high-lift jetflap systems. Rapid convergence as the number of spanwise or chordwise lattices are increased is assured, along with accurate answers. The results from this model should be useful not only in preliminary aircraft design but also, for example, as input for wake vortex roll-up studies and transonic flow calculations.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA. Langley Res. Center Vortex-Lattice Utilization; p 325-342
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 2
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    The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are also given for the case in which the lift and the bending moment about the wing root are fixed while the span is allowed to vary. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span as compared with results for an elliptically loaded wing having the same total lift and bending moment.
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-TN-2249 , Collected Works of Robert T. Jones; p 539-556
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 3
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    Unbekannt
    Tests of the Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Wing Modifications (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius. A short discussion of the results is presented, but no analysis of the data has been made in order to make the data available as soon as possible.
    Schlagwort(e): Spacecraft Design, Testing and Performance
    Materialart: NACA-RM-SA50A05
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
  • 4
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    Unbekannt
    Calibration of Instruments for Measuring Wind Velocity and Direction (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Signal Corps wind equipment AN/GMQ-1 consisting of a 3-cup anemometer and wind vane was calibrated for wind velocities from 1 to 200 miles per hour. Cup-shaft failure prevented calibration at higher wind velocities. The action of the wind vane was checked and found to have very poor directional accuracy below a velocity of 8 miles per hour. After shaft failure was reported to the Signal Corps, the cup rotors were redesigned by strengthening the shafts for better operation at high velocities. The anemometer with the redesigned cup rotors was recalibrated, but cup-shaft failure occurred again at a wind velocity of approximately 220 miles per hour. In the course of this calibration two standard generators were checked for signal output variation, and a wind-speed meter was calibrated for use with each of the redesigned cup rotors. The variation of pressure coefficient with air-flow direction at four orifices on a disk-shaped pitot head was obtained for wind velocities of 37.79 53.6, and 98.9 miles per hour. A pitot-static tube mounted in the nose of a vane was calibrated up to a dynamic pressure of 155 pounds per square foot, or approximately 256 miles per hour,
    Schlagwort(e): Instrumentation and Photography
    Materialart: NACA-RM-SL50I07
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
    BibTip Andere fanden auch interessant ...
    NASA TECHNICAL REPORTS
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