A combined experimental and analytical modeling effort has been carried out to measure the skin friction response of the boundary layer in high Reynolds number adverse pressure gradient flow. The experiment was conducted in the United Technologies Research Center (UTRC) Acoustic Research Tunnel, an ultra-low freestream turbulence facility capable of laminar boundary layer research. Boundary layer computational fluid dynamics and stability modeling were used to provide pre-test predictions, as well as to aid in interpretation of measured results. Measurements were carried out at chord Reynolds numbers 2–3 × 106, with the model set at multiple incidence angles to establish a range of relevant leading edge pressure gradients. The combination of pressure gradient and flight Reynolds number testing on a thin airfoil has produced a unique data set relevant to propulsion system turbomachinery.
Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow
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Holley, BM, Hardin, LW, Tillman, G, Lin, R, & Joo, J. "Skin Friction Measurements of Transition in High Reynolds Number, Adverse Pressure Gradient Flow." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 2A: Turbomachinery. Oslo, Norway. June 11–15, 2018. V02AT39A037. ASME. https://doi.org/10.1115/GT2018-76708
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