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TECHNICAL PAPERS

Flow Characteristics of Transitional Boundary Layers on an Airfoil in Wakes

[+] Author and Article Information
H. Lee, S.-H. Kang

School of Mechanical and Aerospace Engineering, Seoul National University, Seoul 151-742, Korea

J. Fluids Eng 122(3), 522-532 (Feb 14, 2000) (11 pages) doi:10.1115/1.1287592 History: Received February 04, 1999; Revised February 14, 2000
Copyright © 2000 by ASME
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References

Mayle,  R. E., 1991, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113, pp. 509–537.
Walker,  G. J., 1993, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines: A Discussion,” ASME J. Turbomach., 115, pp. 207–217.
Gostelow,  J. P., Blunden,  A. R., and Walker,  G. J., 1994, “Effects of Free-Stream Turbulence and Adverse Pressure Gradients on Boundary Layer Transition,” ASME J. Turbomach., 116, pp. 392–404.
Gostelow,  J. P., and Walker,  G. J., 1991, “Similarity Behavior in Transitional Boundary Layers Over a Range of Adverse Pressure Gradients and Turbulence Levels,” ASME J. Turbomach., 113, pp. 617–625.
Kuan,  C. L., and Wang,  T., 1990, “Investigation of the Intermittent Behavior of Transitional Boundary Layer Using a Conditional Averaging Technique,” Exp. Therm. Fluid Sci., 3, pp. 157–170.
Sohn, K. H., and Reshotko, E., 1991, “Experimental Study of Boundary Layer Transition with Elevated Freestream Turbulence on a Heated Flat Plate,” NASA CR 187068.
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Mislevy,  S. P., and Wang,  T., 1996, “The Effects of Adverse Pressure Gradients on Momentum and Thermal Structures in Transitional Boundary Layers: Part 2—Fluctuation Quantities,” ASME J. Turbomach., 118, pp. 728–736.
Savill, A. M., 1995, Transition Modeling for Turbomachinery III, A Final Summary of ERCOFTAC Transition SIG progress for the 3rd workshop.
Jeon,  W. P., and Kang,  S. H., 1995, “Measurements of Transitional Boundary Layer on a Flat Plate Using a Computational Preston Tube Method,” Exp. Fluids, 20, pp. 29–37.
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Kang, S.-H., Shin, S.-H., Lee, H.-K., and Jeon, W.-P., 1998, “Prediction of Wall Shear Stress in a Transitional Boundary Layer on a Flat Plate Based on the Principle of Computational Preston Tube Method,” 1998, Proceedings of the 4th KSME-JSME Fluids Engineering Conference, Pusan, Korea, pp. 489–492.
Choi, M.-R., Choi, H., and Kang, S.-H., 1998, “Characteristics of the Late-Stage Transition in a Flat Plate Boundary Layer,” Proceedings of the 4th KSME-JSME Fluids Engineering Conference, Pusan, Korea, pp. 481–484.
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Kerho,  M. F., and Bragg,  M. B., 1997, “Airfoil Boundary-Layer Development and Transition With Large Leading-Edge Roughness,” AIAA J., 35, No. 1, pp. 75–84.
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Figures

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Schematic of the arrangement of airfoils
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Comparison of the extended wall law with the DNS data for skin friction
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Distributions of static pressure (a) for single airfoil and (b) for airfoil in wakes (uncertainty for Cp is ±0.015)
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Variations of skin friction for CASE0 (uncertainty for Cf is ±8.4%)
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Profiles of (a) streamwise mean velocity, (b) enlarged view of (a) and (c) rms velocity fluctuation for CASE0 (uncertainties for u+ and u′+ are ±4.8%)
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Power spectral density of velocity fluctuation for CASE0
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Profiles of (a) streamwise mean velocity and (b) turbulence intensities of the upstream wake for CASE1 (uncertainties for u, u′ and v are ±2.96%)
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Variations of skin friction for different Reynolds numbers with respect to (a) chordwise location and (b) Reynolds number based on chordwise location (uncertainty for Cf is ±8.4%)
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Profiles of (a) streamwise mean velocity for CASE1 and (b) enlarged view of (a) (uncertainty for u+ is ±4.8%)
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Profiles of rms velocity fluctuation (a) for CASE1 and (b) for CASE3 (uncertainty for u+ is ±4.8%)
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Streamwise variation of power spectral density for CASE3 at y+=5
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Streamwise mean velocity profiles of incoming wakes (a) for CASE3, (b) for CASE4 and (c) for CASE5 (uncertainty for u is ±2.96%)
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Profiles of turbulence intensities of incoming wakes (a) for CASE3, (b) for CASE4 and (c) for CASE5 (uncertainties for u and v are ±2.96%)
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Variations of skin friction for different airfoil distances (uncertainty for Cf is ±8.4%)
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Profiles of streamwise mean velocity (a) for CASE3, (b) enlarged view of (a), (c) for CASE5 and (d) enlarged view of (c) (uncertainty for u+ is ±4.8%)
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Profiles of rms velocity fluctuation for CASE5 (uncertainty for u′+ is ±4.8%)
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Skewness profiles (a) for CASE3, (b) for CASE4 and (c) for CASE5 (uncertainty for S is ±7.05%)
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Velocity signals at y/δ=0.1 for CASE0
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Velocity signals near the wall (y+=5) for CASE3

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