Quasi-Steady Modeling of Ice Accretion on a Helicopter Fuselage in Forward Flight

Fouladi, Habibollah; Habashi, Wagdi G.; Ozcer, Isik

doi:10.2514/1.c032096

Cited by 14 publications

(6 citation statements)

References 7 publications

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“…The water film flow with surface roughness was built, and water film velocity was simplified as a linear distribution normal for roughness wall, which was written as follows [24][25][26][27][28]:…”

Section: Mathematical Modelmentioning

confidence: 99%

The Influence of Angle of Attack on the Icing Distribution Characteristics of DU97 Blade Airfoil Surface for Wind Turbines

Wang,

Lin,

Lin

et al. 2024

Coatings

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This study explores the influence of angle of attack (AOA) on the icing distribution characteristics of asymmetric blade airfoil (DU97) surfaces for wind turbines under icing conditions by numerical simulation. The findings demonstrate a consistence between the simulated ice shapes and experimental data. The ice thickness distribution on the lower surface of the leading edge exhibits a trend of first rising and then declining along the chord direction while showing a gradually decreasing trend on the upper surface. The ice distribution range on the upper surface of the trailing edge is broader than that on the lower surface. The peak ice thickness at the trailing edge rises significantly as AOA increases from 5° to 10°, and at the leading edge raises dramatically at droplet sizes of 30–40 μm and wind speeds of 5–10 m/s. The peak ice thickness is more significantly influenced by AOA than by ambient temperature due to the combined effect of airflow characteristics induced by AOA and latent heat (phase change) and sensible heat (thermal convection and thermal radiation) caused by ambient temperature. The findings offer valuable insights into the flow and heat transfer physics, and can operate as references for wind turbine anti/de-icing technology.

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Section: Mathematical Modelmentioning

confidence: 99%

The Influence of Angle of Attack on the Icing Distribution Characteristics of DU97 Blade Airfoil Surface for Wind Turbines

Wang,

Lin,

Lin

et al. 2024

Coatings

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show abstract

“…It is employed by several industry standard tools such as LEWICE and FENSAP's ICE3D. FENSAP, developed by Habashi et al [2][3][4][5][6][7][8] is able to use structured, unstructured as well as hybrid meshes for its ice accretion calculations. The droplet code employed by it is called DROP3D, which is a fully-three dimensional Eulerian approach for air flows containing water droplets.…”

Section: Literature Reviewmentioning

confidence: 99%

“…Considering the complex geometry, unstructured grids were used for the simulations. Fouladi et al [8] carried out ice accretion studies on the Robin fuselage using FENSAP. Significant ice accretion was predicted, near the nose of the fuselage, after an ice accretion time of 30 minutes.…”

Section: Literature Reviewmentioning

confidence: 99%

Application of Extended Messinger Models to Complex Geometries

Gupta

Sankar

Kreeger

2020

SAE Technical Paper Series

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Since, ice accretion can significantly degrade the performance and the stability of an airborne vehicle, it is imperative to be able to model it accurately. While ice accretion studies have been performed on airplane wings and helicopter blades in abundance, there are few that attempt to model the process on more complex geometries such as fuselages. This paper proposes a methodology that extends an existing in-house Extended Messinger solver to complex geometries by introducing the capability to work with unstructured grids and carry out spatial surface streamwise marching.For the work presented here commercial solvers such as STAR-CCM+ and ANSYS Fluent are used for the flow field and droplet dispersed phase computations. The ice accretion is carried out using an in-house icing solver called GT-ICE. The predictions by GT-ICE are compared to available experimental data, or to predictions by other solvers such as LEWICE and STAR-CCM+. Three different cases with varying levels of complexity are presented. The first case considered is a commercial transport airfoil, followed by a three-dimensional MS(1)-317 swept wing. Finally, ice accretion calculations performed on a Robin fuselage have been discussed. Good agreement with experimental data, where applicable, is observed. Differences between the ice accretion predictions by different solvers have been discussed.

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“…Khurram and Minhas [10] studied the effects of ice impact on the helicopter body and other materials such as the human skull. They first used FENSAP-ICE for ice accretion on the Caradonna hover test case [11]. The ice breakup analysis solution from Zhang's work [1] was then used to acquire a cracked ice shape.…”

Section: Introductionmentioning

confidence: 99%

Helicopter Rotor Ice Shedding and Trajectory Analyses in Forward Flight

Anthony

Habashi

2021

Journal of Aircraft

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Ice accretion on a helicopter's aerodynamic surfaces during flight can lead to incidents and fatal accidents. An iced helicopter blade results in a decrease in stall angle, an increase in required torque, as well as potential damage from shed ice. While the high centrifugal forces on a rotor may serve as a natural deicing mechanism, they can also lead to uneven ice shedding, causing rotor imbalances or hitting other blades, the fuselage, or the tail rotor. Computational methods are important for predicting in-flight ice formation and are a vital tool in the design of ice protection systems. The objective of this paper is to present a computationally inexpensive methodology to determine for a helicopter in forward flight, following a period of ice accretion, rotor ice crack locations, shedding times, and potential impact zones.

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Quasi-Steady Modeling of Ice Accretion on a Helicopter Fuselage in Forward Flight

Cited by 14 publications

References 7 publications

The Influence of Angle of Attack on the Icing Distribution Characteristics of DU97 Blade Airfoil Surface for Wind Turbines

The Influence of Angle of Attack on the Icing Distribution Characteristics of DU97 Blade Airfoil Surface for Wind Turbines

Application of Extended Messinger Models to Complex Geometries

Helicopter Rotor Ice Shedding and Trajectory Analyses in Forward Flight

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