Analysis of airfoil transitional separation bubbles

Davis, Robert L.; Carter, J.

doi:10.2514/6.1984-1613

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1986

2004

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Cited by 12 publications

(1 citation statement)

References 13 publications

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“…If there is no wall transpiration, 1/Jw = 0, then the boundary conditions (21) given in equations (20) and (21) revert back to those given in equation (16).…”

Section: Transition Predictionmentioning

confidence: 99%

Analysis of transitional separation bubbles on infinite swept wings

Davis¹,

Carter²,

Reshotko

1987

AIAA Journal

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“…If there is no wall transpiration, 1/Jw = 0, then the boundary conditions (21) given in equations (20) and (21) revert back to those given in equation (16).…”

Section: Transition Predictionmentioning

confidence: 99%

Analysis of transitional separation bubbles on infinite swept wings

Davis¹,

Carter²,

Reshotko

1987

AIAA Journal

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Airfoils with separation and the resulting wakes

Cebeci

Clark²,

Chang³

et al. 1986

J. Fluid Mech.

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A viscous/inviscid interaction method is described and has been used to calculate flows around four distinctly different airfoils as a function of angle of attack. It comprises an inviscid-flow method based on conformal mapping, a boundary-layer procedure based on the numerical solution of differential equations and an algebraic eddy viscosity. The results are in close agreement with experiment up to angles close to stall. In one case, where the airfoil thickness is large, small difficulties were experienced and are described. The method is shown to be capable of obtaining results with large flow separation and quantifies the role of transition on the lift coefficient.

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Wind Tunnel Aerodynamic Tests of Six Airfoils for Use on Small Wind Turbines

Selig

McGranahan

2004

Journal of Solar Energy Engineering

183

110

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This paper presents detailed wind tunnel tests data taken on six airfoils having application to small wind turbines. In particular, lift, drag and moment measurements were taken at Reynolds numbers of 100,000, 200,000, 350,000 and 500,000 for both clean and rough conditions. In some cases, data were also taken at a Reynolds number of 150,000. The airfoils included the E387, FX 63-137, S822, S834, SD2030, and SH3055. Prior to carrying out the tests, wind tunnel flow quality measurements were taken to document the low Reynolds number test environment. Oil flow visualization data and performance data taken on the E387 compare favorably with measurements taken at NASA Langley in the Low Turbulence Pressure Tunnel. Highlights of the performance characteristics of the other five airfoils are presented.

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Analysis of airfoil transitional separation bubbles

Cited by 12 publications

References 13 publications

Analysis of transitional separation bubbles on infinite swept wings

Analysis of transitional separation bubbles on infinite swept wings

Airfoils with separation and the resulting wakes

Wind Tunnel Aerodynamic Tests of Six Airfoils for Use on Small Wind Turbines

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