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  • 1
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    A skin friction gauge for impulsive flows (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new skin friction gauge has been designed for use in impulsive facilities. The gauge was tested in the T4 free piston shock tunnel, at the University of Queensland, using a 1.5 m long plate that formed one of the inner walls of a rectangular duct. The test gas was fair and the test section free stream flow had a stagnation enthalpy of 4.7 MJ/kg. Measurements were conducted in a laminar and turbulent boundary layer. The measurements compared well with laminar and turbulent analytical theory.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 95-3152 , Shock Tunnel Studies of Scramjet Phenomena 1994; 9 p|AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 10, 1995 - Jul 12, 1995; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Development of a skin friction gauge for use in an impulse facility (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Tests of a prototype skin friction gauge at Mach 3.2 in a small free piston shock tunnel demonstrate the effectiveness of the design concept and the calibration against theoretical skin friction values in a simple flow. The gauge has a rise time of about 20 microsec, sufficiently short for most shock tunnel applications and approaching the rise times needed for expansion tube applications.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: In: Shock waves; Proceedings of the 18th International Symposium, Sendai, Japan, July 21-26, 1991. Vol. 2 (A93-45451 19-34); p. 967-972.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Skin-friction gauge for use in hypervelocity impulse facilities (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: A transducer is presented which can measure as rise-time of about 20 microsec, and is thereby applicable to measurements in the high-enthalpy flows associated with hypervelocity impulse facilities. Results are presented which demonstrate the effectiveness of the concept in the case of skin-friction measurements conducted on a flat plate at Mach 3.2. The calibration used was against theoretical skin-friction values in a simple flow.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Journal (ISSN 0001-1452); 30; 844
    Format: text
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