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Correlation of Boundary Layer Stability Analysis with Flight Transition Data

  • F. S. CollierJr.
  • D. W. Bartlett
  • R. D. Wagner
  • V. V. Tat
  • B. T. Anderson
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Abstract

Recently, the NASA completed a boundary-layer transition flight test on an F-14 aircraft which has variable sweep capability. Transition data were acquired for a wide variety of sweep angles, pressure distributions, Mach numbers, and Reynolds numbers. In this paper, the F-14 flight test is briefly described and N-factor correlations with measured transition locations are presented for one of two gloves flown on the F-14 wing in the flight program; a thin foam and fiberglass glove which provided a smooth sailplane finish on the basic F-14, modified NACA 6-series airfoil. For these correlations, an improved linear boundary-layer stability theory was utilized that accounts for compressibility and surface and streamline curvature effects for the flow past swept wings.

Keywords

Mach Number Transition Data Pressure Coefficient Laminar Boundary Layer Flight Test 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 1990

Authors and Affiliations

  • F. S. CollierJr.
    • 1
  • D. W. Bartlett
    • 2
  • R. D. Wagner
    • 2
  • V. V. Tat
    • 2
  • B. T. Anderson
    • 3
  1. 1.High Technology CorporationHamptonUSA
  2. 2.NASA Langley Research CenterHamptonUSA
  3. 3.NASA Dryden Flight Research FacilityEdwards AFBUSA

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