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- W303055081 abstract "Oscillating, and post-stall static, airfoil experiments were conducted to test the frequency response of shear-stress-sensitive/temperature-insensitive liquid crystal coatings. The airfoil was a natural-laminar-flow profile designed specifically for vertical axis wind turbine applications (the SAND 0018/50). A full-span model of this contour was exposed to incompressible flows at a freestream Reynolds number (based on chord) of 1.0 {times} 10{sup 6}. Angle-of-attack forcing function was a sine wave of amplitude {plus minus} 10{degree} about a mean angle of 0{degree}. Frequencies of oscillation were 0.2, 0.6 and 1.2 hertz, corresponding to reduced frequencies of 0.006, 0.018 and 0.037. Post-stall static experiments were conducted at a fixed angle of attack of 14{degree}, a condition that yielded unsteady leading-edge separation phenomena. Data acquisition was accomplished by video recording. Observations of boundary layer transition zone movement and unsteady leading-edge separation showed the liquid crystal technique capable of visualizing transient surface shear stress events over the stated dynamic range in a continuous and reversible manner, with a color-change response time of less than 0.03 seconds (the framing rate of standard video equipment). 14 refs., 3 figs." @default.
- W303055081 created "2016-06-24" @default.
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- W303055081 date "1989-01-01" @default.
- W303055081 modified "2023-09-26" @default.
- W303055081 title "Visualization of boundary layer transition zone movement on oscillating airfoils with shear-sensitive liquid crystal coatings." @default.
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