Modelling the effect of step and roughness features on swept wing boundary layer instabilities

Cooke, Emma E.

doi:10.25560/83744

Cited by 2 publications

(3 citation statements)

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“…As a result, current efforts into simulating transitional mechanisms often use high fidelity simulation in a near-body, reduced domain which is embedded in a outer domain encompassing the whole geometry where a lower fidelity model is applied. (See [2] [3,4] [5,6] [7] [8].) Unlike in a large domain where the inflow and outflow boundaries are far away from the geometry of interest so that uniform freestream values can be enforced for the boundary conditions, simple boundary conditions are not available on the reduced domain.…”

Section: Introductionmentioning

confidence: 99%

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Stable, entropy-pressure compatible subsonic Riemann boundary condition for embedded DG compressible flow simulations

Lyu¹,

Chen²,

Du³

et al. 2022

Preprint

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One approach to reducing the computational cost of simulating transitional compressible boundary layer flow is to adopt a near body reduced domain with boundary conditions enforced to be compatible with a computationally cheaper three-dimensional RANS simulation. In such an approach it is desirable to enforce a consistent pressure distribution which is not typically the case when using the standard Riemann inflow boundary conditions. We therefore revisit

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Section: Introductionmentioning

confidence: 99%

“…The RANS result can then be interpolated along the boundary of the reduced domain to provide appropriate distributions, e.g. Cooke [4], Tempelmann [2], and other references mentioned above. In these studies, the velocity distributions at the inflow boundary (of the C-type mesh) are interpolated.…”

Section: Introductionmentioning

confidence: 99%

Stable, entropy-pressure compatible subsonic Riemann boundary condition for embedded DG compressible flow simulations

Lyu¹,

Chen²,

Du³

et al. 2022

Preprint

View full text Add to dashboard Cite

show abstract

“…On clean geometries the baseflow can be computed by a computationally fast and cheap boundary layer solver. Then the disturbance fields are solved according to the Linear Stability Theory (LST) or Parabolized Stability Equations (PSE) [1], and the transition prediction analysis can then be undertaken. However, the baseflow over geometries with sufficiently large imperfection such as steps and gaps, cannot typically be computed through a boundary layer equations solver particularly in the presence of local recirculation, i.e.…”

Section: Introductionmentioning

confidence: 99%

Open-source Framework for Transonic Boundary Layer Natural Transition Analysis over Complex Geometries in Nektar++

Lyu¹,

Chen²,

Du³

et al. 2022

Preprint

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We introduce an open-source and unified framework for transition analysis for laminar boundary layer natural transition at transonic conditions and over complex geometries, where surface irregularities may be present. Different computational tools are integrated in the framework, and therefore overcomes the difficulties of two separate and usually quite disparate processes when using 𝑒 𝑁 method for transition analysis. To generate a baseflow with desired pressure distribution, appropriate pressure compatible inflow boundary condition needs to be developed and enforced. We first derive the system for 1D numerical stability analysis for boundary conditions, and construct three types of pressure compatible inflow. We demonstrate that the entropy-pressure compatible inflow is stable unlike other choices. Compared with the steady baseflow computation, the unsteady simulation for the disturbance field is more challenging for compressible flows because of complex wave reflections, which can easily contaminate the results. We therefore introduce the two main sources of wave decontamination and corresponding methods to obtain clean signal. The workflow within the framework is then verified by computing the disturbance development in 2D flat plate boundary layer flows at Mach 0.8. The 𝑁-factors over a clean flat plate and a flat plate with a forward-facing step are generated, and agree well with the results from the reference. Following the verified workflow, We then analyze the disturbance growth on a wing section of the CRM-NLF model. The 𝑁-factor on a 2D simulation is generated and studied.

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Modelling the effect of step and roughness features on swept wing boundary layer instabilities

Cited by 2 publications

References 0 publications

Stable, entropy-pressure compatible subsonic Riemann boundary condition for embedded DG compressible flow simulations

Stable, entropy-pressure compatible subsonic Riemann boundary condition for embedded DG compressible flow simulations

Open-source Framework for Transonic Boundary Layer Natural Transition Analysis over Complex Geometries in Nektar++

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