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
Link To Document :
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