Boundary layer transition detection by luminescence imagingIn recent experiments we have demonstrated the feasibility of a new approach to boundary layer transition detection. This new approach employs the temperature dependence of certain photoluminescent materials in the form of a surface coating or 'paint' to detect the change in heat transfer characteristics that accompany boundary layer transition. The feasibility experiments were conducted for low subsonic to transonic Mach numbers on two-dimensional airfoil and flat plate configurations. Paint derived transition locations were determined and compared to those obtained from Preston pressure probe measurements. Artificial heating of the models was used to obtain transition temperature signatures suitable for the instrumentation available to us. Initial estimates show, however, that passive kinetic heating at high Mach numbers is a promising alternative.
Document ID
19930046516
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mclachlan, B. G. (NASA Ames Research Center Moffett Field, CA, United States)
Bell, J. H. (NASA Ames Research Center Moffett Field, CA, United States)
Gallery, J. (NASA Ames Research Center Moffett Field, CA, United States)
Gouterman, M. (NASA Ames Research Center Moffett Field, CA, United States)
Callis, J. (Washington Univ. Seattle, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 93-0177
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit