• DocumentCode
    3230530
  • Title

    Application of temperature sensitive paint for detection of boundary layer transition

  • Author

    Popernack, Thomas G., Jr. ; Owens, Lewis R. ; Hamner, Marvine P. ; Morris, Martin J.

  • Author_Institution
    NASA Langley Res. Center, Hampton, VA, USA
  • fYear
    1997
  • fDate
    29 Sep-2 Oct 1997
  • Firstpage
    77
  • Lastpage
    83
  • Abstract
    Temperature sensitive paint systems exploit the variation in convective heat transfer associated with changes from laminar to turbulent flow for detection of boundary layer transition. For this detection technique, it is important for wind tunnel models to have slow thermal response relative to convection heat transfer. Wind tunnels that can produce rapid changes in freestream temperature can create a model thermal response allowing temperature sensitive paint to indicate transition. Numerical heat transfer simulations provide acceptable estimates to assess test techniques and model thermal characteristics. Data are presented to substantiate that the desired test condition could be achieved for a period of time sufficient to document the boundary layer state
  • Keywords
    aerodynamics; boundary layers; forced convection; laminar flow; laminar to turbulent transitions; wind tunnels; boundary layer state; boundary layer transition; convective heat transfer; freestream temperature; heat transfer simulations; temperature sensitive paint; test techniques; thermal response; wind tunnel models; Acoustic signal detection; Aerospace engineering; Cryogenics; Heat transfer; NASA; Numerical simulation; Paints; Temperature distribution; Temperature sensors; Testing;
  • fLanguage
    English
  • Publisher
    ieee
  • Conference_Titel
    Instrumentation in Aerospace Simulation Facilities, 1997. ICIASF '97 Record., International Congress on
  • Conference_Location
    Pacific Grove, CA
  • Print_ISBN
    0-7803-4167-8
  • Type

    conf

  • DOI
    10.1109/ICIASF.1997.644666
  • Filename
    644666