Direct measurements of skin friction in a scramjet combustorA direction experimental measurement was made of the skin friction in the turbulent boundary layer of three-dimensional supersonic combustor flows. A floating element configuration was designed to detect two components of the small tangential shear forces due to the flow passing over a nonobtrusive instrument. A cantilevered sensing head extending from a very sensitive piezoresistive displacement transducer simultaneously measured displacement in the axial and transverse directions to the flow. The small overall deflection means that no self-nulling is required. Consistently repeatable output from the gage during testing show the skin friction with supersonic combustion is higher than for a corresponding noncombusting flow. The results are probably accurate to within 10 percent for the mean streamwise component.
Document ID
19900055077
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Deturris, D. J. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Schetz, J. A. (Virginia Polytechnic Institute and State University Blacksburg, United States)
Hellbaum, R. F. (NASA Langley Research Center Hampton, VA, United States)