Comparing Multi-Element Airfoil Flow Solutions Using Multiple Solvers with Output-Based Adapted Meshes

Galbraith, Marshall C.; Ursachi, Carmen-Ioana; Chandel, Durgesh; Allmaras, Steven R.; Darmofal, David L.; Glasby, Ryan S.; Stefanski, Douglas L.; Erwin, Jon T.; Holst, Kevin R.; Hereth, Ethan A.; Mukhopadhaya, Jayant; Alonso, Juan J.

doi:10.2514/1.j060861

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Medium Adapted Mesh Anisotropic Ratio1

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Cited by 8 publications

(1 citation statement)

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“…However, in our case, this adaptation is less important than the refinements obtained with dual error estimates. 9 Table 1 provides anisotropic ratio mesh characteristics for both adapted meshes. Similarly to inviscid flows, we note that anisotropy increases with the mesh complexity.…”

Section: Medium Adapted Mesh Anisotropic Ratiomentioning

confidence: 99%

Some progress on CFD high lift prediction using metric-based anisotropic mesh adaptation

Alauzet

Clerici

Loseille

et al. 2022

AIAA SCITECH 2022 Forum

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Section: Medium Adapted Mesh Anisotropic Ratiomentioning

confidence: 99%

Some progress on CFD high lift prediction using metric-based anisotropic mesh adaptation

Alauzet

Clerici

Loseille

et al. 2022

AIAA SCITECH 2022 Forum

View full text Add to dashboard Cite

Extension of methods based on the stabilized finite element formulation for the solution of the Navier–Stokes equations and application to aerodynamic design

Chalot,

Johan,

Mallet

et al. 2023

Computer Methods in Applied Mechanics and Engineering

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Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft

Chen,

Galbraith,

Spakovszky

et al. 2023

Journal of Turbomachinery

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This paper presents conceptual design guidelines and results for a tail-integrated propulsion system for a turbo-electric civil transport aircraft with boundary layer ingestion (BLI). The aerodynamic performance goal is separation-free and shock-free operation at cruise with fuel burn reduction, compared with a baseline conventional aircraft for the same mission. The assessment of BLI benefits is based on calculations using CFD and TASOPT software, both to characterize the design challenges and to establish the physical mechanisms for resolving these challenges. The guidelines include a “horseshoe” inlet to accept the non-uniform flow without incurring separation, a nacelle profile similar to supercritical airfoils to reduce shock strength, and an annular nozzle to eliminate flow separation between tail-BLI propulsors. The conceptual design has nine BLI propulsors with electric fans on an axisymmetric tail of a single-aisle aircraft. The fans are powered by twin underwing turbofans. The estimated benefit of the tail-BLI, twin underwing turbofan aircraft is 10.4% in Payload-Range Fuel Consumption (PRFC) at a cruise Mach number of 0.8, compared to a baseline twin underwing turbofan configuration. Sensitivity studies further show that a 1% increase in installed (i.e. with BLI) fan isentropic efficiency translates to 0.8% rise in PRFC benefit.

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Comparing Multi-Element Airfoil Flow Solutions Using Multiple Solvers with Output-Based Adapted Meshes

Cited by 8 publications

References 34 publications

Some progress on CFD high lift prediction using metric-based anisotropic mesh adaptation

Some progress on CFD high lift prediction using metric-based anisotropic mesh adaptation

Extension of methods based on the stabilized finite element formulation for the solution of the Navier–Stokes equations and application to aerodynamic design

Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft

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