Ice Shedding Phenomenon: an Experimental and Numerical Investigation

Enache, Adriana; Bernay, Bruno; Glabeke, Gertjan; Planquart, Philippe; Beeck, Jeroen van

doi:10.2514/6.2020-2817

Cited by 8 publications

(2 citation statements)

References 15 publications

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“…In de-icing mode, the surface is heated periodically, allowing for ice to build up in between the heating cycles. This intercycle ice is removed from the airframe by two processes [13,14]. First, ice at the interface to the surface is melted, resulting in a liquid water layer.…”

Section: Introductionmentioning

confidence: 99%

Experimental Heat Loads for Electrothermal Anti-Icing and De-Icing on UAVs

Hann

Enache

Nielsen³

et al. 2021

Aerospace

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Atmospheric in-flight icing on unmanned aerial vehicles (UAVs) is a significant hazard. UAVs that are not equipped with ice protection systems are usually limited to operations within visual line of sight or to weather conditions without icing risk. As many military and commercial UAV missions require flights beyond visual line of sight and into adverse weather conditions, energy-efficient ice protection systems are required. In this experimental study, two electro-thermal ice protection systems for fixed-wing UAVs were tested. One system was operated in anti-icing and de-icing mode, and the other system was designed as a parting strip de-icing system. Experiments were conducted in an icing wind tunnel facility for varying icing conditions at low Reynolds numbers. A parametric study over the ice shedding time was used to identify the most energy-efficient operation mode. The results showed that longer intercycle durations led to higher efficiencies and that de-icing with a parting strip was superior compared to anti-icing and de-icing without a parting strip. These findings are relevant for the development of energy-efficient systems in the future.

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Section: Introductionmentioning

confidence: 99%

Experimental Heat Loads for Electrothermal Anti-Icing and De-Icing on UAVs

Hann

Enache

Nielsen³

et al. 2021

Aerospace

Self Cite

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“…The parting strip is a heating element located at the leading edge of the wing and is heated continuously to prevent ice accretion at the leading edge. When the other heating zones are activated, not all ice must be melted but the ice will shed when the water film between the wing surface and the remaining ice is of sufficient size [8,16]. This is because the aerodynamic forces push the ice from the wing.…”

Section: Introductionmentioning

confidence: 99%

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Wallisch¹,

Hann²

2023

SAE Technical Paper Series

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<div class="section abstract"><div class="htmlview paragraph">Atmospheric in-flight icing poses a challenge to all aircraft including unmanned aerial vehicles (UAVs). Aircraft should avoid icing conditions unless they have ways of mitigating the negative effects of icing, e.g., if they are equipped with an ice protection system (IPS). When de-icing systems are used, a certain amount of ice is allowed to accumulate before it is removed. This intercycle ice deteriorates the aerodynamics by reducing the lift, adding mass, and increasing the drag. This study combines the energy that is required to compensate for the added drag of intercycle ice shapes with the energy required for a wing IPS and compares the energy needs for different IPS operations. Two different kinds of intercycle ice shapes are simulated numerically using FENSAP-ICE, one ice shape that would accrete on an unprotected wing and one ice shape that would accrete when using a parting strip, a continuously heated element at the leading edge. The results show that both intercycle ice shapes deteriorate the aerodynamic performance of the airfoil significantly compared to a clean airfoil. Additionally, the results show that the aerodynamics deteriorate fastest in the initial stages of ice accretion, likely caused by fast horn growth and a fast transition from laminar to turbulent flow. The aerodynamic performance is combined with energy requirements of electrothermal de-icing tests in an icing wind tunnel. The results show that de-icing with a parting strip is more energy-efficient than de-icing without a parting strip and anti-icing. In addition, it is found that the energy required for the IPS on a wing is significantly larger than the energy required to compensate for the added intercycle drag. Considering these results during the development and operation of an IPS will help to improve the range and endurance of UAVs in icing conditions.</div></div>

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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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Ice Shedding Phenomenon: an Experimental and Numerical Investigation

Cited by 8 publications

References 15 publications

Experimental Heat Loads for Electrothermal Anti-Icing and De-Icing on UAVs

Experimental Heat Loads for Electrothermal Anti-Icing and De-Icing on UAVs

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Numerical simulation of ice shedding motion characteristic on airfoil surface

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