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  • Aircraft Stability and Control; Aerodynamics  (1)
  • GENERAL  (1)
  • Polymer and Materials Science  (1)
  • 1
    ISSN: 0022-3832
    Keywords: Chemistry ; Polymer and Materials Science
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Physics
    Notes: The formulas used for calculation of diffusion coefficients in free diffusion are stated. The calculations request the 0th, first, and second moments of the curve to be calculated. This is usually made by calculation of moments of segments of the figure between the curve and the base line, followed by summation.It is proposed to replace this rather laborious procedure by the use of an integrator. A survey is given on the theoretical background and the principles for such instruments. Some equations are stated for the type of instrument used in these investigations. From these equations it is possible, by inserting the values in the formulas used for the calculation of diffusion coefficients, to express the latter for a certain curve as a function of the rotation of the three integration rolls in the instrument. The relative influence on the final result for these integration rolls is considered. For one of the rolls this can be shown to be insignificant, when the moment axis is chosen very near the central axis of the curve. Our experience has shown the standard error in a normal measurement to be 2 × 10-3 and 3 × 10-3 of a revolution for the two other integration rolls. Some curves are given which show the requests one must put on the relative number of rotations for these rolls to make certain that the relative standard error, introduced by the integrator, will not exceed certain values on the final result. The curves are drawn for values from 2 to 0.1%.From a known Gaussian distribution a set of diffusion curves is drawn. The diffusion coefficient is calculated from these curves both by the usual method and by the integrator. The results obtained by the integrator compare well with those by the usual method if the peaks are not drawn too narrow.
    Additional Material: 6 Ill.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2019-06-28
    Description: A method is described for naming the Space Station Freedom nodes and truss members that enhances the management, maintenance, and record keeping methods utilized by the space station.
    Keywords: GENERAL
    Type: NASA-TM-101594 , NAS 1.15:101594
    Format: application/pdf
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  • 3
    Publication Date: 2019-07-12
    Description: For nearly a century Ludwig Prandtl's lifting-line theory remains a standard tool for understanding and analyzing aircraft wings. The tool, said Prandtl, initially points to the elliptical spanload as the most efficient wing choice, and it, too, has become the standard in aviation. Having no other model, avian researchers have used the elliptical spanload virtually since its introduction. Yet over the last half-century, research in bird flight has generated increasing data incongruous with the elliptical spanload. In 1933 Prandtl published a little-known paper presenting a superior spanload: any other solution produces greater drag. We argue that this second spanload is the correct model for bird flight data. Based on research we present a unifying theory for superior efficiency and coordinated control in a single solution. Specifically, Prandtl's second spanload offers the only solution to three aspects of bird flight: how birds are able to turn and maneuver without a vertical tail; why birds fly in formation with their wingtips overlapped; and why narrow wingtips do not result in wingtip stall. We performed research using two experimental aircraft designed in accordance with the fundamentals of Prandtl's second paper, but applying recent developments, to validate the various potentials of the new spanload, to wit: as an alternative for avian researchers, to demonstrate the concept of proverse yaw, and to offer a new method of aircraft control and efficiency.
    Keywords: Aircraft Stability and Control; Aerodynamics
    Type: NASA/TP-2016-219072 , DFRC-E-DAA-TN19884
    Format: application/pdf
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