Simulation of Ice Shedding Around an Airfoil

Beaugendre, Héloïse; Morency, François; Gallizio, Federico

doi:10.2514/6.2010-7984

Cited by 4 publications

(2 citation statements)

References 11 publications

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“…For further details regarding the numerical method, we refer to the PhD thesis of Gallizio 19 and Beaugendre et al 20 This method would be used to generate "snapshots" required for developing a reduced order model using POD. The details regarding POD is outlined in the following section.…”

Section: Methodsmentioning

confidence: 99%

Calculation of Ice Chunk Trajectory Using Proper Orthogonal Decomposition

Yapalparvi

Beaugendre

Morency

2012

4th AIAA Atmospheric and Space Environments Conference

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In this work, calculation of trajectories of ice chunk are carried out at varying values of ratio of density of ice piece to that of the ambient fluid. Proper Orthogonal Decomposition with Interpolation (PODI) method is then applied on snapshots of trajectories simulated by computational fluid dynamics. Snapshots of trajectories are obtained based on cartesian grids, penalization, and level sets. The extracted POD modes from snapshots are then used to reconstruct solutions and capabilities of POD with interpolation are demonstrated on ice trajectory calculations for flow around iced airfoil and cylinder for density ratio's that are not part of the snapshot set.

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Section: Methodsmentioning

confidence: 99%

Calculation of Ice Chunk Trajectory Using Proper Orthogonal Decomposition

Yapalparvi

Beaugendre

Morency

2012

4th AIAA Atmospheric and Space Environments Conference

Self Cite

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“…A number of anti-icing and de-icing methods are developed or under developing for preventing ice forming and removing ice from aircrafts [2]. Piezoelectric de-icing technique has been studied over ten years, but only a little progress has been made in the laboratory [3].…”

Section: Introductionmentioning

confidence: 99%

Analysis of the Application of Piezoelectric Ceramic Material in the De-Icing Technique of the Aircrafts

Zhu

2017

KEM

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The application of piezoelectric ceramic material in de-icing technique of aircrafts is presented in numerical simulation and experiment methods. Firstly, the ice properties are introduced briefly as the evaluation of device design. Then, modal simulation of the testing skin of NACA 0030 is performed to determine the position where the piezoelectric ceramics fix. The resonance frequency as the driving frequency in the experiment is calculated in harmonic analysis with the actuators bonding on the testing skin model. Moreover, piezoelectric de-icing rig is fabricated as the modeling results. It is shown that the driving frequency agrees well with the calculated resonance frequency, and the ice can be removed when the driving frequency is 1530 Hz and the driving voltage is 650 V. In addition, design factors as material properties, size of the ceramics, and excitation voltage are discussed. From the numerical calculation, the stress will vary with different piezoelectric ceramic materials and sizes of the ceramics. It will decrease with the increase of thickness of the piezoelectric ceramics, but increase linearly with the increase of the voltage. Therefore it is considerable to choose design parameters for piezoelectric de-icing systems.

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Numerical simulation of ice shedding motion characteristic on airfoil surface

et al. 2023

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In order to accurately predict the motion trajectory of ice shedding and ensure the safe flight of aircraft, the motion characteristics of ice shedding under two-dimensional (2D) and three-dimensional (3D) conditions are simulated and analyzed. Considering the influence of any possible shape of shedding ice and its rotation and the magnitude and direction of acceleration with time under aerodynamic force, a six degree-of-freedom analysis method is introduced in this paper. This paper proposes a theoretical model, which can be used to calculate the 3D trajectory of ice shedding with arbitrary shape. The dynamic analysis of real 3D shedding ice is carried out, and the motion behavior of shedding ice with different positions and shapes is calculated. The results show that the movement mode of the shedding ice after leaving the aircraft is translation and rotation. The shape of the low-speed region on the leeward side of the shedding ice will first increase, then decrease, and then increase with the rotation of the ice body. The influence of ice shape on ice shedding trajectory is mainly that the shedding ice continues to flip during the downstream movement of the flow field, and the projected area of the effective windward area in the lift and the drag direction changes with time. The average deviation of the shedding ice at position 5 along the spanwise is only 22.9% of that at position 1. Finally, the closer the initial position of ice shedding is to the airfoil root, the greater the probability of ice shedding hitting the aircraft fuselage. In this paper, the probability of ice shedding hitting the aircraft fuselage is 8%, which all occurred in the case with position 1 as the initial position of ice shedding.

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Simulation of Ice Shedding Around an Airfoil

Cited by 4 publications

References 11 publications

Calculation of Ice Chunk Trajectory Using Proper Orthogonal Decomposition

Calculation of Ice Chunk Trajectory Using Proper Orthogonal Decomposition

Analysis of the Application of Piezoelectric Ceramic Material in the De-Icing Technique of the Aircrafts

Numerical simulation of ice shedding motion characteristic on airfoil surface

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