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  • 1
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    Low aspect ratio wing code validation experiment (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 10; p. 1744-1752.
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Low aspect ratio wing experiment (1994)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: This test was initiated to provide validation data on low aspect ratio wings at transonic speeds. The test was conducted so that the data obtained would be useful in the validation of codes, and all boundary condition data required would be measured as part of the test. During the conduct of the test, the measured quantities were checked for repeatability, and when the data would not repeat, the cause was tracked down and either eliminated or included in the measurement uncertainty. The accuracy of the data was in the end limited by wall imperfections of the wind tunnel in which the test was run.
    Keywords: AERODYNAMICS
    Type: AGARD, A Selection of Experimental Test Cases for the Validation of CFD Codes, Volume 2; 11 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental studies of shock wave/wall jet interaction in hypersonic flow (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The interaction between a planar shock wave and a wall jet produced by slot cooling in turbulent hypersonic flow was experimentally studied. Detailed distributions of heat transfer and pressure are obtained in the incident shock/wall jet interaction region for a series of shock strengths and impingement positions for two nozzle heights. The major result is that the cooling film could be readily dispersed by relatively weak incident shocks such that the peak heating in the recompression region was not significantly reduced by even the largest levels of film cooling. Regions of boundary layer separation were induced in the film cooling layer, the size of which first increased and then decreased with increasing film cooling. The size of the separated regions and magnitude of the recompression heating were not strongly influenced by the thickness of the cooling film or point of shock impingement relative to the exit plane of the nozzles.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-0607
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Low aspect ratio wing code validation experiment (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An experiment was performed on a low-aspect ratio wing to define the limits of the validity of codes which are used to predict the flow over modern fighter configurations. The focus of the experiment is to provide data at or near the true operating conditions of transonic aircraft. The Reynolds numbers reached in this experiment reproduce those experienced by an aircraft with a 5-m root chord, flying at 14 to 16 km, from Mach 0.6 to 0.8. The angle-of-attack range of the experiment extends into the regime of leading-edge separation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-0402
    Format: text
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    NASA TECHNICAL REPORTS
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