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  • 1
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    Incompressible boundary-layer stability analysis of LFC experimental data for sub-critical Mach numbers (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An incompressible boundary-layer stability analysis of Laminar Flow Control (LFC) experimental data was completed and the results are presented. This analysis was undertaken for three reasons: to study laminar boundary-layer stability on a modern swept LFC airfoil; to calculate incompressible design limits of linear stability theory as applied to a modern airfoil at high subsonic speeds; and to verify the use of linear stability theory as a design tool. The experimental data were taken from the slotted LFC experiment recently completed in the NASA Langley 8-Foot Transonic Pressure Tunnel. Linear stability theory was applied and the results were compared with transition data to arrive at correlated n-factors. Results of the analysis showed that for the configuration and cases studied, Tollmien-Schlichting (TS) amplification was the dominating disturbance influencing transition. For these cases, incompressible linear stability theory correlated with an n-factor for TS waves of approximately 10 at transition. The n-factor method correlated rather consistently to this value despite a number of non-ideal conditions which indicates the method is useful as a design tool for advanced laminar flow airfoils.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3999 , NAS 1.26:3999
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A unique measurement technique to study laminar-separation bubble characteristics on an airfoil (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A 'nonintrusive', multielement heat-transfer sensor was designed to study laminar-separation bubble characteristics on a NASA LRN (1)-1010 low-Reynolds number airfoil. The sensor consists of 30 individual nickel films, vacuum-deposited on a thin substrate (0.05 mm) that was bonded to the airfoil model with the sensor array placed streamwise on the airfoil upper surface. Experiments were conducted on a 15-cm chord model in the 50,000-300,000 chord Reynolds number range. Time history as well as spectral analysis of signals from surface film gauges were simultaneously obtained to determine the location of laminar separation and the subsequent behavior of the separated shear layer. In addition to the successful determination of laminar separation, a new phenomenon involving a large phase shift in dynamic shear stresses across the separation and reattachment points was observed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-1271
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Overview of X-38 Hypersonic Aerothermodynamic Wind Tunnel Data and Comparison with Numerical Results (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A NASA team of engineers has been organized to design a crew return vehicle for returning International Space Station crew members from orbit. The hypersonic aerothermodynamic characteristics of the X-23/X-24A derived X-38 crew return vehicle are being evaluated in various wind tunnels in support of this effort. Aerothermodynamic data from two NASA hypersonic tunnels at Mach 6 and Mach 10 has been obtained with cast ceramic models and a thermographic phosphorus digital imaging system. General windward surface heating features are described based on experimental surface heating images and surface oil flow patterns for the nominal hypersonic aerodynamic orientation. Body flap reattachment heating levels are examined. Computational Fluid Dynamics tools have been applied at the appropriate wind tunnel conditions to make comparisons with this data.
    Keywords: Aerodynamics
    Type: AIAA Paper 97-2475 , 32nd AIAA Thermophysics Conference; Jun 23, 1997 - Jun 25, 1997; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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