The Effects of Adverse Pressure Gradients on Momentum and Thermal Structures in Transitional Boundary Layers: Part 2 — Fluctuation Quantities

Mislevy, Scott P.; Wang, Ting

doi:10.1115/95-gt-005

Cited by 3 publications

(1 citation statement)

References 30 publications

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“…The computed u profile at this location shows a good qualitative match with its experimental counterpart and, in particular, exhibits a plateau in the region 10 y 30, albeit less marked than in the experiment. Mislevy and Wang [43] showed that this plateau in the early stages of transition is due to the presence of an adverse pressure gradient by comparing fluctuation profiles in transitioning boundary layers subject to different adverse pressure gradients. The height at which the maximum fluctuation levels are reached is slightly lower in the computational results, at approximately y ' 30, to be compared with the value of y ' 40 obtained experimentally.…”

Section: A Mean Flowfieldmentioning

confidence: 99%

Direct Noise Computation of the Turbulent Flow Around a Zero-Incidence Airfoil

2008

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A large eddy simulation of the flow around a NACA 0012 airfoil at zero incidence is performed at a chord-based Reynolds number of 500,000 and a Mach number of 0.22. The aim is to show that high-order numerical schemes can successfully be used to perform direct acoustic computations of compressible transitional flow on curvilinear grids. At a Reynolds number of 500,000, the boundary layers around the airfoil transition from an initially laminar state to a turbulent state before reaching the trailing edge. Results obtained in the large eddy simulation show a well-placed transition zone and turbulence levels in the boundary layers that are in agreement with experimental data. Furthermore, the radiated acoustic field is determined directly by the large eddy simulation, without the use of an acoustic analogy. Third-octave acoustic spectra are compared favorably with experimental data.

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Section: A Mean Flowfieldmentioning

confidence: 99%

Direct Noise Computation of the Turbulent Flow Around a Zero-Incidence Airfoil

2008

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Heat transfer and skin-friction in a turbulent boundary layer under a non-equilibrium longitudinal adverse pressure gradient

Kiselev

Leontiev

Vinogradov

et al. 2021

International Journal of Heat and Fluid Flow

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Detailed Boundary Layer Measurements on a Turbine Stator Vane at Elevated Freestream Turbulence Levels

Radomsky

Thole

2001

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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High freestream turbulence levels have been shown to greatly augment the heat transfer on a gas turbine airfoil. To better understand these effects, this study has examined the effects elevated freestream turbulence levels have on the boundary layer development along a stator vane airfoil. Low freestream turbulence measurements (0.6%) were performed as a baseline for comparison to measurements at combustor simulated turbulence levels (19.5%). A two-component LDV system was used for detailed boundary layer measurements of both the mean and fluctuating velocities on the pressure and suction surfaces. Although the mean velocity profiles appeared to be more consistent with laminar profiles, large velocity fluctuations were measured in the boundary layer along the pressure side at the high freestream turbulence conditions. Along the suction side, transition occurred further upstream due to freestream turbulence.

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The Effects of Adverse Pressure Gradients on Momentum and Thermal Structures in Transitional Boundary Layers: Part 2 — Fluctuation Quantities

Cited by 3 publications

References 30 publications

Direct Noise Computation of the Turbulent Flow Around a Zero-Incidence Airfoil

Direct Noise Computation of the Turbulent Flow Around a Zero-Incidence Airfoil

Heat transfer and skin-friction in a turbulent boundary layer under a non-equilibrium longitudinal adverse pressure gradient

Detailed Boundary Layer Measurements on a Turbine Stator Vane at Elevated Freestream Turbulence Levels

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