Comparison of Computational and Experimental Ice Accretions of Large Swept Wings

Fujiwara, Gustavo E. C.; Bragg, Michael B.; Broeren, Andy P.

doi:10.2514/1.c035631

Cited by 20 publications

(3 citation statements)

References 51 publications

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“…These experiments led to the establishing of a database including a large number of ice shapes that can accrete on aircraft wings in different operating conditions [16][17][18][19]. The comparison of numerical predictions against observations allows for model testing and for their fine-tuning [20][21][22], including the investigation of wind tunnel effects on ice accretion experiments [23] and the investigation of the aerodynamics of a swept wing with leading-edge ice accretion [24][25][26][27][28].…”

Section: Introductionmentioning

confidence: 99%

Modeling In-Flight Ice Accretion Under Uncertain Conditions

Gori¹,

Congedo²,

Maître

et al. 2022

Journal of Aircraft

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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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Section: Introductionmentioning

confidence: 99%

Modeling In-Flight Ice Accretion Under Uncertain Conditions

Gori¹,

Congedo²,

Maître

et al. 2022

Journal of Aircraft

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“…The studies apply to both ice-induced aerodynamic degradation [85,86] and shedding debris [87,88]. Initially carried out experimentally [38,45,89], ice accretion studies have been supplemented by numerical simulations with the increase of computational power [52,90,91].…”

Section: The Ice Accretion Process: a Roughness-dependent Phenomenonmentioning

confidence: 99%

Surface Roughness in RANS Applied to Aircraft Ice Accretion Simulation: A Review

Ignatowicz,

Morency,

Beaugendre

2023

Fluids

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Experimental and numerical fluid dynamics studies highlight a change of flow structure in the presence of surface roughness. The changes involve both wall heat transfer and skin friction, and are mainly restricted to the inner region of the boundary layer. Aircraft in-flight icing is a typical application where rough surfaces play an important role in the airflow structure and the subsequent ice growth. The objective of this work is to investigate how surface roughness is tackled in RANS with wall resolved boundary layers for aeronautics applications, with a focus on ice-induced roughness. The literature review shows that semi-empirical correlations were calibrated on experimental data to model flow changes in the presence of roughness. The correlations for RANS do not explicitly resolve the individual roughness. They principally involve turbulence model modifications to account for changes in the velocity and temperature profiles in the near-wall region. The equivalent sand grain roughness (ESGR) approach emerges as a popular metric to characterize roughness and is employed as a length scale for the RANS model. For in-flight icing, correlations were developed, accounting for both surface geometry and atmospheric conditions. Despite these research efforts, uncertainties are present in some specific conditions, where space and time roughness variations make the simulations difficult to calibrate. Research that addresses this gap could help improve ice accretion predictions.

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“…Generally, ice can be divided into glaze ice and rime ice according to ice temperature and liquid water content. For rime ice, as the temperature is low, water droplets will freeze immediately when they hit the airfoil [25] and ice accretion gradually increases along the flow direction at the leading edge; the ice does not radically alter the shape of the airfoil; however, it does increase the chord length of the airfoil. So rime ice is a good test case to compare if the droplet trajectory impact locations and icing limits of hybrid and full-scale 15 International Journal of Aerospace Engineering airfoil were the same [26].…”

Section: Ice Accretion and Ice-induced Vortices Ofmentioning

confidence: 99%

A Parametric Design Method for Hybrid Airfoils for Icing Wind Tunnel Test

Yang

Tong

et al. 2021

International Journal of Aerospace Engineering

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The size of aircraft models that can be tested in icing wind tunnels is limited by the dimensions of the facilities in present; it is an effective method to replace the large model with a hybrid airfoil to carry out the experiment. A design method of multiple control points for hybrid airfoil based on the similarity of flow field in the leading edge of airfoil is proposed. Aiming at generating the full-scale flow field and ice accretion on the leading edge, multiobjective genetic optimization algorithm is used to design the hybrid airfoil under different conditions by combining the airfoil parameterization and solution of spatial constraint. Pressure tests of hybrid airfoils are carried out and compared with the leading edge pressure of the corresponding full-scale airfoils. The design and experimental results show that the pressure coefficient deviation between the hybrid airfoils designed and the corresponding full-scale airfoil in the 15% chord length range of the leading edge is within 4%. Finally, the vortex distribution and ice accretion process of the two airfoils were simulated by the unsteady Reynolds-averaged-Navier–Stokes (URANS) equations and multistep ice numerical method; it is shown that the hybrid airfoil can provide the same vortex distribution and ice accretion with the full-scale airfoil.

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Comparison of Computational and Experimental Ice Accretions of Large Swept Wings

Cited by 20 publications

References 51 publications

Modeling In-Flight Ice Accretion Under Uncertain Conditions

Modeling In-Flight Ice Accretion Under Uncertain Conditions

Surface Roughness in RANS Applied to Aircraft Ice Accretion Simulation: A Review

A Parametric Design Method for Hybrid Airfoils for Icing Wind Tunnel Test

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