Calculation of Viscous Drag and Turbulent Boundary-Layer Separation on Two-Dimensional and Axisymetric Bodies in Incompressible Flows

Cebeci, Tuncer; Mosinskis, G.; Smith, Andrew

doi:10.21236/ad0720775

Cited by 5 publications

(3 citation statements)

References 7 publications

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“…• In this case, we replace x by (x -x') in (7), and take the value of R x as u m (x m -x')lv. Then x m -x' is given by 5 With the expression given by Eq. (8), Eq.…”

Section: Stratford's Methodsmentioning

confidence: 99%

Calculation of Separation Points in Incompressible Turbulent Flows

Cebeci¹,

Mosinskis²,

Smith³

1972

Journal of Aircraft

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The purpose of this paper is to evaluate the accuracy with which the location of turbulent separation can be predicted on two-dimensional and axisymmetric bodies. The evaluation was made by studying a considerable number of flows that had separation. Calculated separation points were compared with the experimentally measured location. Four methods of predicting separation in turbulent flow were evaluated. They were Goldschmied's method, Stratford's method, Head's method, and the Cebeci-Smith method. It was concluded from the study that the last three listed methods predict separation points with the reliability and accuracy needed for aerodynamic design purposes.Nomenclature c =chord c f = local skin friction coefficient, r w /(l/2)pw e 2 C p = pressure coefficient, (p -p m )l(l/2pu m 2 ) D = diameter h = total head H = shape factor, S*/d k = mixing-length constant L = reference body length p = pressure R c = chord-Reynolds number, u^cjv R D = diameter-Reynolds number, u^Djv R L = length-Reynolds number, u^L/v R x = local Reynolds number, u e x/v R 0 = Reynolds number, ujdjv u,v = x and y components of velocity, respectively #* = friction velocity, (r w /p) 1/2 x -streamwise distance y = distance normal to the surface of the body a = angle of attack 8 = boundary-layer thickness 8* = displacement thickness, J^ (1 -u/u e )dy 6 = momentum thickness, J^ u/u e (l -u/u e )dy IJL = dynamic viscosity v = kinematic viscosity p = density r = shear stress (/> = angle from stagnation point Subscripts e = edge of the boundary layer m = minimum pressure point sep = separation point tr = transition w = wall co = freestream conditions

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“…• In this case, we replace x by (x -x') in (7), and take the value of R x as u m (x m -x')lv. Then x m -x' is given by 5 With the expression given by Eq. (8), Eq.…”

Section: Stratford's Methodsmentioning

confidence: 99%

Calculation of Separation Points in Incompressible Turbulent Flows

Cebeci¹,

Mosinskis²,

Smith³

1972

Journal of Aircraft

Self Cite

View full text Add to dashboard Cite

show abstract

“…In order to determine where the flow around a body is likely to detach, there are numerous methods in the literature that combine approximate boundary layer solutions and empirical data to derive practical separation criteria [37,38] . In this work, Stratford's method [39] is used.…”

Section: Flow Detachment Correctionmentioning

confidence: 99%

“…Extensions to account for compressibility effects can be also found in [38]. In the present work, the guidelines given in [37,42] are followed with the objective to emphasizing the implementation aspects.…”

Section: Prediction Of Separation Pointsmentioning

confidence: 99%