Curved laser-sheet for conformal surface flow diagnostics

Estevadeordal, Jordi; Marks, Christopher R.; Sondergaard, Rolf; Wolff, Mitch

doi:10.1007/s00348-010-0967-0

Cited by 4 publications

(2 citation statements)

References 12 publications

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“…Several researchers [22,23] have successfully applied 2D planar PIV in the spanwise direction plane parallel to the suction side of an airfoil (or flat plate with adverse pressure gradient [24]) by taking advantage of the low curvature of the blade in the region of interest. Curved laser-sheet PIV has been reported as well [2,15]. It has also been obtained by spanwise scanning PIV near the wall and through a separation bubble on the suction side of a SD7003 airfoil at Reynolds numbers of 2.0 × 10 4 -6.0 × 10 4 [22].…”

Section: Methodsmentioning

confidence: 76%

“…In an attempt to better understand the three-dimensionality (3D) of complex flows and obtain the third velocity component, a variety of techniques have been devised [14]. Examples include stereoscopic PIV, tomographic PIV, holographic PIV, dual-plane PIV, and curved laser sheet methods [15]. Most of the abovementioned techniques require specialized calibration or image correlation methods beyond those typically used for 2D single plane PIV.…”

Section: Introductionmentioning

confidence: 99%

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Study of Leading-Edge Dimple Effects on Airfoil Flow Using Tomographic PIV and Temperature Sensitive Paint

Stolt

Ullah

Estevadeordal

2019

Fluids

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Airfoil blades can experience a significant change of angle of attack during operation cycles, which may lead to static or dynamic stall in various applications. It is unclear how elements distributed at the leading edge would affect the aerodynamic performance and stall behaviors. In the present study, a distributed dimples configuration was investigated and compared to a baseline smooth NACA0015 airfoil at low Reynolds numbers. Two- and four-camera, tomographic particle image velocimetry (PIV), and temperature sensitive paint (TSP) techniques were set up to gather flow and surface information near the curved leading-edge surface and to study flow separation. Results suggest that distributed dimples configuration create abrupt separation leading to stall and induce a similar stall compared to the smooth model. However, the stall is induced more abruptly and with different flow patterns. Results show that patterns of separated shear layer at stalled conditions were enhanced by the current configuration. Effect of these structures on the boundary layer transition were also analyzed based on combined tomographic PIV and TSP measurement techniques.

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