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  • Other Sources  (3)
  • 1950-1954  (3)
  • 1952  (3)
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  • 1950-1954  (3)
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  • 1
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    Theoretical analysis of hydrodynamic impact of a prismatic float having freedom in trim (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-2698
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    The Langley Annular Transonic Tunnel (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report describes the development of the Langley annular transonic tunnel, a facility in which test Mach numbers from 0.6 to slightly over 1.0 are achieved by rotating the test model in an annular passage between two concentric cylinders. Data obtained for two-dimensional airfoil models in the Langley annular transonic tunnel at subsonic and sonic speeds are shown to be in reasonable agreement with experimental data from other sources and with theory when comparisons are made for nonlifting conditions or for equal normal-force coefficients rather than for equal angles of attack. The trends of pressure distributions obtained from measurements in the Langley annular transonic tunnel are consistent with distributions calculated for Prandtl-Meyer flow.
    Type: NACA-TR-1106
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Hydrodynamic Impact of a System with a Single Elastic Mode II : Comparison of Experimental Force and Response with Theory (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Hydrodynamic impact tests were made on an elastic model approximating a two-mass spring system to determine experimentally the effects of structural flexibility on the hydrodynamic loads encountered during seaplane landing impacts and to correlate the results with theory. A flexible seaplane was represented by a two-mass spring system consisting of a rigid prismatic float connected to a rigid upper mass by an elastic structure. The model had a ratio of sprung mass to hull mass of 0.6 and a natural frequency of 3.0 cycles per second. The tests were conducted in smooth water at fixed trims and included both high and low flight-path angles and a range of velocity. Theoretical and experimental comparisons indicated that the theoretical results agreed well with the experimental results.
    Type: NACA-TR-1075
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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