FENSAP-ICE: Analytical Model for Spatial and Temporal Evolution of In-Flight Icing Roughness

Croce, Giulio; Candido, Erika De; Habashi, Wagdi G.; Munzar, Jeffrey D.; Aubé, Martin S.; Baruzzi, Guido S.; Aliaga, Cristhian

doi:10.2514/1.47143

Cited by 42 publications

(13 citation statements)

References 15 publications

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“…In addition, this would be done in an integrated way, i.e., as a system (airplane propellers, helicopter rotors, airplane jetengine), and not by reducing dimensions (airfoil sections rather than wing) or isolating components (rotor alone for example). The methodology ought to prove an able recipient of any new, empirical, or analytical, ice surface roughness data that varies in both space and time [21].…”

Section: Discussionmentioning

confidence: 99%

FENSAP-ICE-Unsteady: Unified In-Flight Icing Simulation Methodology for Aircraft, Rotorcraft, and Jet Engines

Aliaga¹,

Aubé²,

Baruzzi³

et al. 2011

Journal of Aircraft

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In-flight ice accretion, even though driven by a steady flow airstream, is an inherently unsteady phenomenon. It is, however, completely ignored in icing simulation codes (one-shot) or, at best approximated via quasi-steady modeling (multishot). The final ice shapes thus depend on the length of the total accretion time (one-shot), or of the arbitrarily prescribed time intervals (multishot), during which the impact of ice growth on both airflow and water impingement is ignored. Such a longstanding heuristic approximation is removed in this paper by coupling in time the dilute two-phase flow (air and water droplets flow) with ice accretion, and is implemented in a new code, FENSAP-ICE-Unsteady. The two-phase flow is solved using the coupled Navier-Stokes and water concentration equations, and the water film characteristics and ice shapes are obtained from laws of conservation of mass and energy within the thin film layer. To continually update the geometry of the iced surface in time, arbitrary Lagrangian-Eulerian terms are added to all governing equations to account for mesh movement in the case of stationary components. In the case of rotating/stationary interacting components, a dynamically stitched grid is used. The numerical results clearly show that unsteady modeling improves the accuracy of both rime and glaze ice shape prediction, compared with the traditional quasi-steady approach with frozen solutions. The unsteady model is shown to open the door for a unified approach to icing on fixed wings, on helicopters with blades/rotors/fuselage systems. Problems of current concern in the icing community such as the ingestion of ice crystals at high altitude become tractable with the new formulation.

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Section: Discussionmentioning

confidence: 99%

FENSAP-ICE-Unsteady: Unified In-Flight Icing Simulation Methodology for Aircraft, Rotorcraft, and Jet Engines

Aliaga¹,

Aubé²,

Baruzzi³

et al. 2011

Journal of Aircraft

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“…The hemispherical-bead model calculates roughness height based on aerodynamic shear stress, gravity forces and the pressure gradient along the blade profile [14]. The high tip velocity on the SPFM rotor contributes to a high aerodynamic shear stress component on the blade, reducing the roughness of ice when compared to the AERTS rotor.…”

Section: Fig 18 Rotor Performance Summary Via Experimental and Numermentioning

confidence: 99%

“…An additional degradation factor, surface roughness, is applied through a model that approximates ice growth as hemispherical beads [14]. The inertia attributed to the growth of ice on the blade is considered by including several point masses along the blade at the appropriate chord-wise locations.…”

mentioning

confidence: 99%

Ice Accretion Effects on Helicopter Rotor Performance, via Multibody and CFD Approaches

Kelly¹,

Habashi²,

Quaranta³

et al. 2018

Journal of Aircraft

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“…Furthermore, the disjoining pressure model, usually adopted to model the contact line singularity, has been validated in the framework of moving film front, while, excluding the precursor work of Schwartz and Eley [8], its capability to properly model the droplet dynamics and the receding contact lines has not been tested yet. On the other side, the evolution of a liquid layer over a solid surface is involved in a number of engineering applications, such as in-flight icing on the aircraft surface, where the ice accretion is driven by the evolution of a droplet population [9], or absorption/distillation processes IOP Publishing doi:10.1088/1742-6596/2177/1/012043 2 through structured packing [10,11]. Here the governing lubrication equations are numerically solved using an in-house code, previously developed and validated by the Authors [10,12].…”

Section: Introductionmentioning

confidence: 99%

Numerical modelization of contact angle hysteresis of falling droplet under enhanced lubrication approximation

Suzzi

Croce

2022

J. Phys.: Conf. Ser.

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Moving contact lines are involved in several engineering applications: in in-flight icing phenomenon, the eventual transition from droplet to rivulet or continuous film regime is crucial for the prediction of ice accretion over the aircraft surface; absorption process through structured packing is also characterized by a thin film flowing over the corrugated sheets. Disjoining pressure together with the assumption of a thin precursor film is largely used in numerical simulations of thin films and moving droplets in order to model the dynamics of moving contact lines and the surface wettability properties, in terms of imposed static contact angle. The disjoining pressure model was largely validated in case of falling films with the well known Voinov-Hoffman-Tanner law. On the other side, the capability of the disjoining pressure to model the contact angle hysteresis, which is a crucial parameter for predicting moving droplets behavior, has not been discussed yet. Here, numerical simulations of both falling films and moving droplets under lubrication approximation are conducted and the disjoining pressure model is used to predict the contact line dynamics. After verification of the full curvature implementation for a 1D falling film, the effective contact angle hysteresis is estimated for a moving droplet under different flow conditions and the transition from droplet to rivulet regime detected.

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FENSAP-ICE: Analytical Model for Spatial and Temporal Evolution of In-Flight Icing Roughness

Cited by 42 publications

References 15 publications

FENSAP-ICE-Unsteady: Unified In-Flight Icing Simulation Methodology for Aircraft, Rotorcraft, and Jet Engines

FENSAP-ICE-Unsteady: Unified In-Flight Icing Simulation Methodology for Aircraft, Rotorcraft, and Jet Engines

Ice Accretion Effects on Helicopter Rotor Performance, via Multibody and CFD Approaches

Numerical modelization of contact angle hysteresis of falling droplet under enhanced lubrication approximation

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