Abstract
This work employs a shear and stress sensitive film (S3F) to investigate the suction surface flow features associated with a higher-lift low-pressure turbine airfoil (L2F). Well-behaved higher-lift low-pressure turbine designs suffer from an inability to accurately predict the transition location above the suction surface, and the separation onset locations obtained with the S3F sensor herein allow the validation of the separated-flow transition model used in the L2F design cycle. Improvements to the S3F measurement technique are explained in this work, and results are compared over a range of Reynolds numbers at 3.3 % freestream turbulence including skin friction measurements at the trailing edge of the airfoil. Results demonstrate an improvement to the S3F data reduction process by accounting for the tunnel and model vibration, which will allow a greater range of sensor application.
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