Stability-Based Transition Model Using Transport Equations

Pascal, Lucas; Delattre, Grégory; Deniau, Hugues; Cliquet, Julien

doi:10.2514/1.j058906

Cited by 15 publications

(6 citation statements)

References 27 publications

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“…However, the stability-based model and the AHD criterion do not predict the effects of compressibility on the transition region length. For example, the AHD-based transition models developed by Pascal et al [24] and Ströer et al [25, 26] rely on user-specified inputs for the length of the transition region. Further work is required to develop a correlation for the transition length in compressible flows.…”

Section: Compressibility Correctionsmentioning

confidence: 99%

Compressibility corrections to extend a smooth local correlation-based transition model to transonic flows

Piotrowski

Zingg

2023

Aeronaut. j.

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This paper presents progress towards a transition modelling capability for use in the numerical solution of the Reynolds-averaged Navier-Stokes equations that provides accurate predictions for transonic flows and is thus suitable for use in the design of wings for aircraft flying at transonic speeds. To this end, compressibility corrections are developed and investigated to extend commonly used empirical correlations to transonic flight conditions while retaining their accuracy at low speeds. A compressibility correction for Tollmien-Schlichting instabilities is developed and applied to a smooth local correlation-based transition model and a stationary crossflow instability compressibility correction is included by adding a new crossflow source term function. Two- and three-dimensional transonic transition test cases demonstrate that the Tollmien-Schlichting compressibility correction produces substantially improved agreement with the experimental transition locations, particularly for higher Reynolds number applications where the effects of flow compressibility are expected to be more significant, such as the NASA CRM-NLF wing-body configuration, while the crossflow compressibility correction prevents an inaccurate, upstream transition front. The compressibility corrections and modifications do not significantly affect the numerical behaviour of the model, which provides an efficient alternative to non-local and higher-fidelity approaches, and can be applied to other transport-equation-based transition models with low-speed empirical correlations without affecting their predictive capability in the incompressible regime.

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Section: Compressibility Correctionsmentioning

confidence: 99%

Compressibility corrections to extend a smooth local correlation-based transition model to transonic flows

Piotrowski

Zingg

2023

Aeronaut. j.

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“…In this solver, under the RANS formulation, the previously derived intermittency factor model was coupled to the Navier-Stokes equations, to Pascal et al [4]'s transported transition criteria and to the modified version [5] of the Spalart and Allmaras [32]'s one-equation turbulence model. The resulting set of equations reads:…”

Section: A Integration and Coupling Of The Intermittency Factormentioning

confidence: 99%

“…Pascal et al [4] transition model accounts for natural transition induced by Tollmien-Schlichting instabilities (AHD transition criteria [37]) and by transverse transition mechanisms (C1 criterion [22]). It consists of 4 partial differential equations.…”

Section: B Transition Modelmentioning

confidence: 99%

A Transport Equation of the Intermittency Factor for Natural Transition

Taguema

Pascal

Chedevergne

et al. 2022

AIAA AVIATION 2022 Forum

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HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L'archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d'enseignement et de recherche français ou étrangers, des laboratoires publics ou privés.

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“…2) Transition criteria, which utilize empirical criteria derived from theoretical and experiment study, such as AHD (Arnal-Habiballah-Delcourt) criteria [11], Gleyzes criteria [12] and C1 criteria [13]. 3) Transition transport models, which implement empirical transition criteria into flow simulations by means of transport equations, such as γ-Reθ model [14] [15], k-ω-γ model [16] [17] and AFT (amplification factor transport) model [18]. The e N method is firstly proposed in 1956 [2] and then modified for 2D, 3D, incompressible and compressible boundary layers [19].…”

Section: Introductionmentioning

confidence: 99%

Application of surrogate models to stability analysis and transition prediction in hypersonic flows

Nie

Song

Han

et al. 2022

Preprint

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To increase the efficiency and convenience of stability-based transition prediction in flow simulations, simplified methods are introduced to substitute direct stability analyses for rapid disturbance growth prediction. For low-speed boundary layers, these methods are mainly established based on a self-similar assumption, which is not applicable to non-similar hypersonic flows over blunt cones. The objective of this article is to investigate the application of surrogate models to substitute linear stability analysis for non-similar flows on blunt cones, focused on input parameters for boundary-layer (BL) profile description. Firstly, correlations analyses between BL edge and profile parameters are conducted, along with a self-similar analysis and a discrete BL profile analysis, which present four groups of BL characteristic parameters. Secondly, using these parameters as inputs, surrogate models are built for disturbance growth prediction over an MF-1 blunt cone at flight experiments. Results show that, using 4 BL edge parameters and a BL shape factor {Ue, Te, ρe, ηe, H12} can achieve comparable accuracy with using 16 discrete BL profile parameters, which is also more precise than using merely self-similar parameters or BL edge parameters. Thirdly, the established surrogate models are validated in stability analysis and transition prediction over the MF-1 blunt cone at the moments of t =17s~22s in flight experiments. Compared with direct linear stability analyses, the mean relative error of predicted disturbance growth rates by surrogate models is 8.0% and the maximum relative error of N factor envelopes is 6.6%, which indicates the feasibility of using surrogate models to substitute stability analysis in transition prediction of non-similar flows over hypersonic boundary layers.

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Stability-Based Transition Model Using Transport Equations

Cited by 15 publications

References 27 publications

Compressibility corrections to extend a smooth local correlation-based transition model to transonic flows

Compressibility corrections to extend a smooth local correlation-based transition model to transonic flows

A Transport Equation of the Intermittency Factor for Natural Transition

Application of surrogate models to stability analysis and transition prediction in hypersonic flows

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