Boundary Layer Adaptivity for Transonic Turbulent Flows

Chitale, Kedar C.; Sahni, Onkar; Tendulkar, Saurabh; Nastasia, Rocco; Shephard, Mark S.; Jansen, Kenneth E.

doi:10.2514/6.2013-2445

Cited by 12 publications

(6 citation statements)

References 17 publications

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“…In this work, the wall modeling was assumed as a tradeoff between computational resource available and reliability on the results leading to the requirement that the first cell height was beyond the viscous sublayer and into the log-layer or overlap region (y+ ~ 30). In such a way, it was possible to assure that the results were asymptotically converged for drag values (DCd between the configurations) and are expected to be in accordance with other works in literature such as Jongen (1992), Knopp (2006) and Chitale et al (2014) among others, at the time of this research. The next section shows the results obtained with the RANS simulations of these four air-intake geometries at two different angle-of-attack conditions: (AOA = α = 2°) at cruise condition and (AOA = α = 15°) emulating take-off condition.…”

Section: Computational Meshsupporting

confidence: 80%

“…Figure 15 shows in detail the mesh generated in this region for each of the proposed cases. It is also important to say that to simulate boundary layers in turbulent flow requires fine grid spacing near the walls, closely dependent on the choice of the turbulence model (Chitale et al 2014). In this work, the wall modeling was assumed as a tradeoff between computational resource available and reliability on the results leading to the requirement that the first cell height was beyond the viscous sublayer and into the log-layer or overlap region (y+ ~ 30).…”

Section: Computational Meshmentioning

confidence: 99%

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A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

Almeida

Souza

Cunha³

2021

J. Aerosp. Technol. Manag.

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This work presents selected results of an unconventional aircraft development campaign. Engine installation at the rear part of the fuselage imposed design constraints for air intakes that should be used for cooling purposes. Trial and error flight tests increased the development cost and time which required a more sophisticated analysis through computational fluid dynamics (CFD) techniques and robust semiempirical approach. The carried-out investigation of the air intakes started with an empirical approach from guidelines for designing NACA and scoops. Numerical studies via computational fluid dynamics were performed with the air intakes installed in the aircraft fuselage. An analysis based on the air intake efficiency, drag and the effect of angle of attack are detailed in this work. Different air intakes designs, such as scoops of different shapes, were evaluated seeking for improved air intake efficiency and low drag while providing enough air for cooling the engine compartment. The results showed that the numerical approach used herein decreased the development cost and time of the aircraft, providing a reasonable low-cost approach and leading to a design selection more easily. Based on the current approach the canard airplane geometry was changed to account for the new selected air intake for engine cooling purposes.

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Section: Computational Meshsupporting

confidence: 80%

Section: Computational Meshmentioning

confidence: 99%

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

Almeida

Souza

Cunha³

2021

J. Aerosp. Technol. Manag.

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show abstract

“…When using boundary layer meshes as used in this analysis, it is required to either maintain the layered structure during adaptivity or adapt the wall normal direction in such a way so as to create acceptable meshes for the turbulence model. Previous attempts have been made to use flow physics to drive boundary layer mesh adaptation 6 for simpler meshes but such an approach is under development and testing for complex geometries like multi-element wings.…”

Section: Adaptive Analysismentioning

confidence: 99%

Finite Element Flow Simulations of the EUROLIFT DLR-F11 High Lift Configuration

Chitale

Rasquin

Martin

et al. 2014

52nd Aerospace Sciences Meeting

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This paper presents flow simulation results of the EUROLIFT DLR-F11 multi-element wing configuration, obtained with a highly scalable finite element solver, PHASTA. This work was accomplished as a part of the 2 nd high lift prediction workshop. In-house meshes were constructed with increasing mesh density for analysis. A solution adaptive approach was used as an alternative and its effectiveness was studied by comparing its results with the ones obtained with other meshes. Comparisons between the numerical solution obtained with unsteady RANS turbulence model and available experimental results are provided for verification and discussion. Based on the observations, future direction for adaptive research and simulations with higher fidelity turbulence models is outlined.

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“…Boundary layer adaptivity in the thickness direction using physics-based indicators has been carried out for simpler configurations. 6 Anisotropic boundary layer mesh adaptivity is significantly more complex for configurations, such as multi-element wings, than previously studied examples. The challenges are two fold: the surface mesh needs to be adapted anisotropically which presents challenges for complex geometries, and the geometric approximation of the mesh needs to be improved as the mesh is refined which is critical for curved surfaces.…”

Section: Introductionmentioning

confidence: 99%

Anisotropic Boundary Layer Adaptivity of Multi-Element Wings

Chitale

Rasquin

Sahni

et al. 2014

52nd Aerospace Sciences Meeting

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Multi-element wings are popular in the aerospace community due to their high lift performance. Turbulent flow simulations of these configurations require very fine mesh spacings especially near the walls, thereby making use of a boundary layer mesh necessary. However, it is difficult to accurately determine the required mesh resolution a priori to the simulations. In this paper we use an anisotropic adaptive meshing approach including adaptive control of elements in the boundary layers and study its effectiveness for two multielement wing configurations. The results are compared with experimental data as well as nested refinements to show the efficiency of adaptivity driven by error indicators, where superior resolution in wakes and near the tip region through adaptivity are highlighted.

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Boundary Layer Adaptivity for Transonic Turbulent Flows

Cited by 12 publications

References 17 publications

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

Finite Element Flow Simulations of the EUROLIFT DLR-F11 High Lift Configuration

Anisotropic Boundary Layer Adaptivity of Multi-Element Wings

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