Transitional Delayed Detached Eddy Simulation of Multielement, High-Lift Airfoils

Coder, James G.; Ortiz-Melendez, Hector D.

doi:10.2514/6.2018-2846

Cited by 4 publications

(1 citation statement)

References 20 publications

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“…The lack of reliability of current models to predict laminar-to-turbulent transition over the flight envelop of aircraft is still limiting the extent to which design can rely on computational tools, while making costly wind tunnel and flight tests a necessity [2]. Prediction of transition on practical three-dimensional wing geometries using the e N method coupled with laminar boundary layer and linear stability codes [3,4] or local statistical correlation CFD models such as the γ − Re θ Langtry-Menter model [5] have proven challenging [6][7][8], whereas transitional hybrid RANS-LES solvers have shown encouraging but still mitigated results [9][10][11]. The crossflow models implemented in RANS solvers [12,13,15,16] account for the effect of roughness in a somewhat rudimentary way.…”

Section: Introductionmentioning

confidence: 99%

Preliminary scale-resolving simulations of laminar-to-turbulent transition in swept-wing flow

Denison

Garai

Murman

2019

AIAA Aviation 2019 Forum

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Swept wings and control surfaces are common elements of modern aircraft, and it has been shown both experimentally and theoretically that laminar-to-turbulent transition of the three-dimensional boundary layer that develops over them is highly sensitive to surface roughness. Numerous studies have been conducted on the effect of discrete roughness elements or distributed roughness elements on swept flow transition, however so far limited computational effort has been dedicated to the study of transition over swept wings with randomly distributed micron-sized roughness. In the present work, we set up to reproduce the extensive experimental data base generated by Dagenhart et al [1] for the infinite swept wing NLF(2)-0415. To this purpose, we perform scale-resolving simulations of flow transition over smooth and rough surfaces using a high-order space-time spectral-element Discontinuous-Galerkin solver. Different types of surface roughnesses are implemented by elastically deforming the original mesh. The study shows that the experimental results cannot be accounted for by a perfectly smooth wing and reveals a strong sensitivity of the transition process to the representation of the surface roughness. The crossflow patterns and transition location approach those measured for some of the surface profiles, however a correlation between the wavenumber spectrum of the surface, grid resolution and boundary layer stability is yet to be established.

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Section: Introductionmentioning

confidence: 99%

Preliminary scale-resolving simulations of laminar-to-turbulent transition in swept-wing flow

Denison

Garai

Murman

2019

AIAA Aviation 2019 Forum

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Design and Characterization of High-Lift Capabilities for Slotted, Natural-Laminar-Flow Airfoils

Ortiz-Melendez¹,

Long²,

Colletti

et al. 2023

Journal of Aircraft

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Morphing leading-edge shapes are of great interest for natural-laminar-flow airfoils operating in high lift as they can be designed to delay separation without any steps or gaps in the surface geometry. A computational study was performed to explore leading-edge configurations for a high-lift system featuring the S207, slotted, natural-laminar-flow airfoil, which was designed for commercial transport applications. Morphing technology was applied to mitigate abrupt wing-stall characteristics and further increase maximum lift. As a result, significantly higher lift coefficients were obtained. However, signs of wake bursting (i.e., off-body separation and narrow stall region in lift curves) were observed. The high-lift aft element’s position was optimized in a previous study for the S204, a slotted, natural-laminar-flow airfoil designed for business-jet applications. An optimization of S207’s aft element for high-lift is recommended. A constant-width slot between stowed and deployed positions allowed attached flow to be maintained across the aft element, which proved beneficial when combined with leading-edge morphing technology. The use of morphing technology was observed to produce superior high-lift performance over drooped leading edge, as the latter produced detrimental pressure peaks caused by the sharp curvature of the flap-like drooped leading edge’s upper surface that led to compressible stall.

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Computational Investigation on Airframe Noise Generation Around High-lift devices

Moghadam¹,

Lin²,

Jian³

2020

Aiaa Aviation 2020 Forum

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Transitional Delayed Detached Eddy Simulation of Multielement, High-Lift Airfoils

Cited by 4 publications

References 20 publications

Preliminary scale-resolving simulations of laminar-to-turbulent transition in swept-wing flow

Preliminary scale-resolving simulations of laminar-to-turbulent transition in swept-wing flow

Design and Characterization of High-Lift Capabilities for Slotted, Natural-Laminar-Flow Airfoils

Computational Investigation on Airframe Noise Generation Around High-lift devices

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