A transition detection study using a cryogenic hot film system in the Langley 0.3-meter transonic cryogenic tunnelA transition detection study was conducted in the Langley 0.3-Meter Transonic Cryogenic Tunnel (0.3-m TCT) using a specialized hot film system designed specifically for use in cryogenic wind tunnels. The quantitative transition location data obtained at near cryogenic conditions, 360 deg R (200K) represents the first definitive transition Reynolds numbers obtained in a cryogenic wind tunnel. The model was tested at both adiabatic and nonadiabatic wall conditions with a wall-to-total temperature ratio as low as 0.47. The test results indicated an improved technique for hot-film installation and a modified data acquisition system would allow the on-line determination of the location of boundary layer transition in cryogenic wind tunnels, such as the U.S. National Transonic Facility.
Document ID
19870035106
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, C. B. (NASA Langley Research Center Hampton, VA, United States)
Carraway, D. L. (NASA Langley Research Center Hampton, VA, United States)
Stainback, P. C. (NASA Langley Research Center Hampton, VA, United States)
Fancher, M. F. (Douglas Aircraft Co. Long Beach, CA, United States)