Application of Laminar-Turbulent Transition Criteria in Navier-Stokes Computations

Cliquet, Julien; Houdeville, R.; Arnal, D.

doi:10.2514/1.30215

Cited by 65 publications

(54 citation statements)

References 10 publications

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“…Indeed, the fundamental mechanisms of transition processes do not appear as clearly as in stability computations. To calculate the transition location induced by TS instabilities, the Arnal-Habiballah-Delcourt (AHD) criterion has been developed [21][22][23]. This criterion is based on the integration line concept and was originally developed for incompressible flows over adiabatic walls.…”

Section: B Arnal-habiballah-delcourt and Gleyzes Criteriamentioning

confidence: 99%

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

et al. 2015

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The friction component is responsible for more than 40% of typical civil aircraft drag. As a consequence, the issue of laminar flow has been of prime importance in aeronautics for many years now. This article is focused on TollmienSchlichting-induced transition and drag predictions of two-dimensional laminar airfoils obtained with experimental and numerical methods. In 2012, a test campaign in the ONERA-S2MA wind tunnel, including infrared acquisitions, pressure sensors, and wake analyses, allowed substantial data to be obtained on such airfoils in transonic conditions. To complete this study, two-dimensional fluid dynamics computations have been performed, either with a Reynoldsaveraged Navier-Stokes solver using transition criteria or with a boundary-layer code combined with direct stability analysis. Furthermore, experimental (wake survey) and numerical (far-field theory) techniques allowing airfoil drag breakdown have been employed. Wind-tunnel and computational fluid dynamics transition predictions have been compared. Good agreement has been observed but the transition criteria may show some limitations in particular situations, such as long separation bubble development. The gains in lift and drag due to laminar flow have been quantified (natural vs triggered transition). Concerning drag reduction, the importance of the viscous pressure component has been highlighted. Finally, the effects of parameters such as angle of attack, Mach number, and Reynolds number on transition location and drag have been investigated.subscript for local state value f = frequency of boundary-layer instability M = freestream Mach number N T = value of factor N at transition onset P i = stagnation pressure Re = freestream Reynolds number based on the airfoil chord T i = stagnation temperature Tu = turbulence level U, V, W = x, y, z velocity components x, y, z = x, y, z coordinates Y = normalized first cell height Λ 2 = mean Pohlhausen parameter ρ = density Subscript 0 = freestream state value

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Section: B Arnal-habiballah-delcourt and Gleyzes Criteriamentioning

confidence: 99%

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

et al. 2015

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“…ONERA [13] introduced into the elsA code transition criteria for longitudinal and crossflow instabilities. These criteria were developed from results of linear stability and transition correlations.…”

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confidence: 99%

Automatic Transition Predictions Using Simplified Methods

et al. 2009

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Laminar-turbulent transition remains a critical issue in a number of cases, including drag reduction, performance prediction of high-lift systems, improved accuracy in general computational fluid dynamics, and reduction of computation cycles for development of optimization tools. Transition delay remains one of the most promising technologies for reducing air transport energy consumption, through natural or hybrid laminar flow control. The use of linear stability theory, either local or nonlocal, remains rather demanding in terms of knowledge and user interaction. Hence, a demand exists for simplified, robust, and accurate transition prediction tools to be inserted into general flow solvers, of boundary-layer or Reynolds-averaged Navier-Stokes types. The problem can be solved by developing transition criteria or database methods. In this last case, characteristics of an actual flow are derived from known solutions of model flows. ONERA, the French Aerospace Laboratory, has long been involved in the development of such methods, and the present paper aims at providing a comprehensive view of the tools developed in the second category, applicable from low-speed two-dimensional to transonic three-dimensional flows, and even to three-dimensional supersonic flows.

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“…The extremely high computational demands in helicopter simulations driven by a sufficient temporal resolution of the unsteady flow, the high spatial resolution of the flow field to capture the blade vortices and separations at the fuselage, the incorporation of geometrical details (for example, details of the rotor head) and the need for the realization of the rotor rotation (for example, using the chimera technique) have led to highly approximate approaches applying empirical or semi-empirical transition criteria for Tollmien-Schlichting, crossflow and separation-induced transition in formulations for incompressible and compressible flow [26,[61][62][63][64] with integral laminar boundary-layer parameters estimated by simple approximation formulas in structured CFD codes [65][66].…”

Section: Empirical Transition Criteriamentioning

confidence: 99%

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

Krumbein

Krimmelbein

Grabe

et al. 2015

45th AIAA Fluid Dynamics Conference

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Application of Laminar-Turbulent Transition Criteria in Navier-Stokes Computations

Cited by 65 publications

References 10 publications

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

Experimental and Numerical Methods for Transition and Drag Predictions of Laminar Airfoils

Automatic Transition Predictions Using Simplified Methods

Development and Application of Transition Prediction Techniques in an Unstructured CFD Code (Invited)

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