An effect of unit Reynolds number on the laminar-turbulent transition on 3D swept wing with χ = 72° at M = 2

Experimental studies of the influence of unit Reynolds number on the laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge at Mach number 2 are performed. The experiments were performed on a model of a swept wing with a swept angle of the leading edge of 72 degrees and with a 3% profile with a variable chord length in span. The hot-wire measurements showed that a laminar-turbulent transition in a supersonic boundary layer of a swept wing with a subsonic leading edge occurs earlier (~25-30%) than on a model with a supersonic leading edge with the same oncoming flow parameters. It is shown that a change unit Reynolds number insignificant influence the laminar-turbulent transition in the boundary layer of a swept wing with a subsonic leading edge.

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Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow

Thermophysics and Aeromechanics ◽

10.1134/s0869864318050025 ◽

2018 ◽

Vol 25 (5) ◽

pp. 659-665 ◽

Cited By ~ 2

Author(s):

Yu. G. Ermolaev ◽

A. D. Kosinov ◽

A. N. Semenov ◽

N. V. Semionov ◽

A. A. Yatskikh

Keyword(s):

Reynolds Number ◽

Supersonic Flow ◽

Swept Wing ◽

Unit Reynolds Number ◽

Turbulent Transition ◽

Laminar Turbulent Transition

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Unit Reynolds number, Mach number and pressure gradient effects on laminar–turbulent transition in two-dimensional boundary layers

Experiments in Fluids ◽

10.1007/s00348-018-2538-8 ◽

2018 ◽

Vol 59 (5) ◽

Cited By ~ 4

Author(s):

Steffen Risius ◽

Marco Costantini ◽

Stefan Koch ◽

Stefan Hein ◽

Christian Klein

Keyword(s):

Reynolds Number ◽

Mach Number ◽

Pressure Gradient ◽

Boundary Layers ◽

Two Dimensional ◽

Unit Reynolds Number ◽

Turbulent Transition ◽

Dimensional Boundary ◽

Gradient Effects ◽

Laminar Turbulent Transition

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Determining critical Reynolds number of laminar-turbulent transition in a flat Poiseuille problem based on “discontinuous functions” method

Trudy MAI ◽

10.34759/trd-2019-108-3 ◽

2019 ◽

pp. 3-3

Author(s):

Olga Khatuntseva

Keyword(s):

Reynolds Number ◽

Critical Reynolds Number ◽

Discontinuous Functions ◽

Turbulent Transition ◽

Laminar Turbulent Transition

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Common features between the Newtonian laminar–turbulent transition and the viscoelastic drag-reducing turbulence

Journal of Fluid Mechanics ◽

10.1017/jfm.2019.567 ◽

2019 ◽

Vol 877 ◽

pp. 405-428 ◽

Cited By ~ 8

Author(s):

Anselmo S. Pereira ◽

Roney L. Thompson ◽

Gilmar Mompean

Keyword(s):

Reynolds Number ◽

Turbulent Flow ◽

Drag Reduction ◽

Turbulent Flows ◽

Temporal Dynamics ◽

Homoclinic Orbits ◽

Theoretical Development ◽

Transitional Flows ◽

Turbulent Transition ◽

Laminar Turbulent Transition

The transition from laminar to turbulent flows has challenged the scientific community since the seminal work of Reynolds (Phil. Trans. R. Soc. Lond. A, vol. 174, 1883, pp. 935–982). Recently, experimental and numerical investigations on this matter have demonstrated that the spatio-temporal dynamics that are associated with transitional flows belong to the directed percolation class. In the present work, we explore the analysis of laminar–turbulent transition from the perspective of the recent theoretical development that concerns viscoelastic turbulence, i.e. the drag-reducing turbulent flow obtained from adding polymers to a Newtonian fluid. We found remarkable fingerprints of the variety of states that are present in both types of flows, as captured by a series of features that are known to be present in drag-reducing viscoelastic turbulence. In particular, when compared to a Newtonian fully turbulent flow, the universal nature of these flows includes: (i) the statistical dynamics of the alternation between active and hibernating turbulence; (ii) the weakening of elliptical and hyperbolic structures; (iii) the existence of high and low drag reduction regimes with the same boundary; (iv) the relative enhancement of the streamwise-normal stress; and (v) the slope of the energy spectrum decay with respect to the wavenumber. The maximum drag reduction profile was attained in a Newtonian flow with a Reynolds number near the boundary of the laminar regime and in a hibernating state. It is generally conjectured that, as the Reynolds number increases, the dynamics of the intermittency that characterises transitional flows migrate from a situation where heteroclinic connections between the upper and the lower branches of solutions are more frequent to another where homoclinic orbits around the upper solution become the general rule.

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Prediction of Lapse Rate in Low Pressure Turbines With and Without Modeling of the Laminar-Turbulent Transition

Volume 6: Turbo Expo 2007, Parts A and B ◽

10.1115/gt2007-27110 ◽

2007 ◽

Cited By ~ 1

Author(s):

Mahmoud L. Mansour ◽

S. Murthy Konan ◽

Shraman Goswami

Keyword(s):

Reynolds Number ◽

Turbulence Model ◽

Test Data ◽

Low Pressure ◽

Lapse Rate ◽

Test Cases ◽

Low Pressure Turbine ◽

Turbulent Transition ◽

Transition Modeling ◽

Laminar Turbulent Transition

Although turbo-machinery main stream flows are predominantly turbulent, the low pressure turbine airfoil surface boundary layer may be either laminar or turbulent. When boundary layer flow is laminar and passes through a zone of adverse pressure gradient, bypass or separation transition can occur via the Tollmien-Schlichting or Kelvin-Helmholtz instabilities. As the gas turbine’s low pressure turbine operating condition changes from sea level take-off to the altitude cruise, Reynolds number is significantly lowered and the turbine’s performance loss increases significantly. This fall-off in performance characteristic is known as lapse rate. Ability to accurately model such phenomenon is a prerequisite for reliable loss prediction and essential for improving low pressure turbine designs. Establishing such capability requires the validation and evaluation of existing low Reynolds number turbulence models, with laminar-turbulent transition modeling capability, against test cases with measured data. This paper summarizes the results of evaluating and validating two 3D viscous “RANS” Reynolds-Averaged Navier-Stokes programs for two test cases with test data. The first test case is the ERCOFTAC’ flat plate with and without pressure gradient, and the second is a Honeywell three-and-half-stage low pressure turbine with available test data at high and low Reynolds number operations. In addition to evaluating the CFD codes against test data, the flat plate test cases were used to establish the meshing and modeling best practice for each code before performing the validation for the Honeywell multistage low pressure turbine. The RANS CFD programs are Numeca’s Fine Turbo and ANSYS/CFX. Numeca’s Fine Turbo employs a two-equation K-ε turbulence model without laminar-turbulent transition modeling capability and the one-equation Spallart-Allmaras turbulence model with laminar-turbulent transition modeling capability. The ANSYS/CFX, on the other hand, employs a two-equation K-ω turbulence model (AKA SST or shear stress transport) with ability to model laminar-turbulent transition. Predictions of the CFD codes are compared with test data and the impact of modeling the laminar-turbulent transition on the prediction accuracy is assessed and presented. Both CFD codes are commercially available and the evaluation presented here is based on users’ prospective that targets the applicability of such predictive tools in the turbine design process.

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Laminar-Turbulent Transition of a Low Reynolds Number Rigid or Flexible Airfoil

AIAA Journal ◽

10.2514/1.25812 ◽

2007 ◽

Vol 45 (7) ◽

pp. 1501-1513 ◽

Cited By ~ 114

Author(s):

Yongsheng Lian ◽

Wei Shyy

Keyword(s):

Reynolds Number ◽

Low Reynolds Number ◽

Turbulent Transition ◽

Low Reynolds ◽

Laminar Turbulent Transition

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A Numerical Investigation on the Onset of the Various Flow Regimes in a Spherical Annulus

Journal of Fluids Engineering ◽

10.1115/1.4033489 ◽

2016 ◽

Vol 138 (11) ◽

Cited By ~ 2

Author(s):

Lalaoua Adel ◽

Bouabdallah Ahcene

Keyword(s):

Reynolds Number ◽

Flow Behavior ◽

Flow Regimes ◽

Skin Friction Coefficient ◽

Formation Mechanisms ◽

Turbulent Regime ◽

Turbulent Transition ◽

Inner Sphere ◽

Spherical Couette ◽

Laminar Turbulent Transition

The spherical Couette system, consisting of the flow in the annular gap between two concentric rotating spheres, is a convenient problem for studying the laminar–turbulent transition. Many of the transitional phenomena encountered in this flow are of fundamental relevance for the understanding of global processes in the planetary atmospheres as well as in astrophysical and geophysical motions. Furthermore, the study of spherical Couette flow (SCF) is of basic importance in the field of hydrodynamic stability. This paper focuses principally on the numerical prediction of various transitions between flow regimes in a confined spherical gap between a rotating inner sphere and a fixed outer spherical shell. The finite-volume-based computational fluid dynamics, FLUENT software package, is adopted to investigate numerically the flow of a viscous incompressible fluid in the closed spherical gap. Two important dimensionless parameters completely define the flow regimes: the Reynolds number, Re = Ω1R12/ν, for the rotation of the inner sphere and the gap width, β = (R2 − R1)/R1 = 0.1, for the geometry. The numerical calculations are carried out over a range of Reynolds number from two until 60,000. The numerical results are compared with the experimental data available in the literature, and the agreement between the two approaches is very good. The laminar–turbulent transition, the onset of different instabilities, the formation mechanisms of various structures, and the flow behavior are examined and described in detail by the pressure field, meridional streamlines, circumferential velocity, and skin friction coefficient. In addition, the velocity time series and the corresponding power spectral density are considered and analyzed over a large range of Reynolds number. Three kinds of fundamental frequencies expressed by F0, F1, and F2 are obtained corresponding to the spiral mode associated with the wavy mode (SM + WM), the wavy mode (WVF), and the chaotic fluctuation (CF), respectively. However, no sharp fundamental frequency components are observed for the turbulent regime.

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