Boundary Layer Transition- Freestream Turbulence and Pressure Gradient Effects

Driest, E. R. Van; Blumer, C. B.

doi:10.2514/3.1784

Cited by 163 publications

(18 citation statements)

References 2 publications

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“…For example, a Prandtl-Blasius BL becomes linearly unstable for Re BL > 520 (Schmid & Henningson 2001). However, the presence of free-stream turbulence above the BL (as is the case here in TC flow) lowers the transition Reynolds number Re T (van Driest & Blumer 1963;Andersson et al 1999) since such strong disturbances can cause bypass transitions in the BL. Consequently, the marginal stability of the BLs as determined from the TC stability criterion (Esser & Grossmann 1996) is bypassed by a transition to turbulence following another route (Faisst & Eckhardt 2000).…”

Section: Boundary-layer Transitionmentioning

confidence: 81%

Marginally stable and turbulent boundary layers in low-curvature Taylor–Couette flow

Brauckmann

Eckhardt

2017

J. Fluid Mech.

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Marginal stability arguments are used to describe the rotation-number dependence of torque in Taylor-Couette (TC) flow for radius ratios η 0.9 and shear Reynolds number Re S = 2 × 10 4 . With an approximate representation of the mean profile by piecewise linear functions, characterized by the boundary-layer thicknesses at the inner and outer cylinder and the angular momentum in the center, profiles and torques are extracted from the requirement that the boundary layers represent marginally stable TC subsystems and that the torque at the inner and outer cylinder coincide. This model then explains the broad shoulder in the torque as a function of rotation number near R Ω ≈ 0.2. For rotation numbers R Ω < 0.07 the TC stability conditions predict boundary layers in which shear Reynolds numbers are very large. Assuming that the TC instability is bypassed by some shear instability, a second maximum in torque appears, in very good agreement with numerical simulations. The results show that, despite the shortcomings of marginal stability theory in other cases, it can explain quantitatively the non-monotonic torque variation with rotation number for both the broad maximum as well as the narrow maximum.

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Section: Boundary-layer Transitionmentioning

confidence: 81%

Marginally stable and turbulent boundary layers in low-curvature Taylor–Couette flow

Brauckmann

Eckhardt

2017

J. Fluid Mech.

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“…The physical meaning of intermittency is the dimensionless ratio of the time a flow is turbulent compared with a total time. As the transition process depends on nonlocal boundary-layer quantities, which are not portable to RANS-based CFD codes, an assumption of Van Driest and Blumer [13] is used as a starting point to correlate local and nonlocal quantities. The correlation is based on an approximation of the streamwise velocity profile (see for example Schlichting [14]), valid for 2-D boundary-layer flows.…”

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confidence: 99%

Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

Seyfert

Krumbein

2012

Journal of Aircraft

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The correlation-based -Re t transition transport model has been implemented into a hybrid Reynolds-averaged Navier-Stokes solver and evaluated on various test cases. The original model formulation and recently published approaches of different authors for relevant empirical model functions as well as different transition criteria are compared. The prediction of transition with the correlation-based model was applied to a zero pressure gradient flat plate test case and some well-known one-element airfoil test cases. A comparison with the standard approach for transition prediction in the flow solver used based on the e N method was accomplished. The simulation results in terms of transition locations and skin-friction coefficient distributions, performance, and limiting factors of both transition prediction methods for the various test cases are presented and discussed.function that controls the transition length k = turbulent kinetic energy k amb = lower bound for turbulent kinetic energy in the far field M = Mach number N = critical N factor Re x = Reynolds number based on axial coordinate x Re c = Reynolds number based on momentum thickness, critical Re t = Reynolds number based on momentum thickness at transition onset Re = Reynolds number based on momentum thickness Re = Reynolds number based on vorticity Tu = local turbulence intensity Tu 0 = turbulence intensity at the far-field boundary Tu 1 = freestream turbulence intensity U = local velocity x = axial coordinate y = distance in wall coordinates = angle of attack = model constant for the shear-stress transport k-! turbulence model = model constant for the supersonic transport k-! turbulence model = intermittency = molecular viscosity t = eddy viscosity = density ! = specific turbulent dissipation rate ! amb = lower bound for turbulent dissipation rate in the far field

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“…As it is indicated in [4], VanDriestBlumer parameter [26] VDB max = max(Re v ) 2.193Re θ is a weakly changing function (within the range 0.951.4) of boundary layer shape factor H sf = δ * /θ that also changes only slightly (for §ows considered in [4]): −2.2 < H sf < 3.6 near the value speci¦c for Blasius pro¦le H sf = 2.59 and depends, mainly, on pressure gradient. For supersonic and hypersonic §ows, this situation changes drastically.…”

Section: Transition Prediction Using Reynolds-averaged Navierstokes Ementioning

confidence: 97%

“…(13) for intermittency γ ¤switches on¥ at that point and γ starts growing (and turbulent kinetic energy starts increasing together with it) and transition begins. As it follows from (14), intermittency starts to grow at that point within the boundary layer where function Re v /Re θ reaches its maximum according to VanDriestBlumer model [26].…”

Section: Transition Prediction Using Reynolds-averaged Navierstokes Ementioning

confidence: 99%

On modeling of laminar-turbulent transition in supersonic flows with engineering correlations and Reynolds-averaged Navier-Stokes equations

Kovalev

Kudryavtsev

Churakov

2015

Progress in Flight Physics – Volume 7

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This paper deals with di¨erent engineering correlations for prediction of transitional hypersonic §ows both for transition onset prediction and transition zone description. In spite of recent progress in simulation of stability equations and direct methods, these approaches remain main tool in everyday design practice. Very close approach is using correlations incorporated in the Reynolds-averaged NavierStokes (RANS) equations, e. g., γRe θ transition model. But this model has some limitations when applied to supersonic §ows and some approaches for subduing these limitations are considered. Also, the e¨ect of local heating/cooling on laminarturbulent transition (LTT) on sharp cone is analyzed on the basis of both algebraic correlations and RANS models.

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Boundary Layer Transition- Freestream Turbulence and Pressure Gradient Effects

Cited by 163 publications

References 2 publications

Marginally stable and turbulent boundary layers in low-curvature Taylor–Couette flow

Marginally stable and turbulent boundary layers in low-curvature Taylor–Couette flow

Evaluation of a Correlation-Based Transition Model and Comparison with the eN Method

On modeling of laminar-turbulent transition in supersonic flows with engineering correlations and Reynolds-averaged Navier-Stokes equations

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