UAV Icing: Numerical Simulation of Icing Effects on Wing and Empennage

Lindner, Markus H.; Wallisch, Joachim; Hann, Richard

doi:10.4271/2023-01-1384

Cited by 2 publications

(1 citation statement)

References 14 publications

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“…Finally, the study only considers added drag because of ice accretion on wings and the IPS power required to protect the wings. Other parts of the aircraft, for example icing on the empennage [46], are not included in the study. Some recommendations for the operation of IPS systems and future work can be drawn from this study.…”

Section: The Required Energy For Flight In Icing Conditionsmentioning

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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Section: The Required Energy For Flight In Icing Conditionsmentioning

confidence: 99%

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Wallisch¹,

Hann²

2023

SAE Technical Paper Series

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Numerical Investigation on Intermittent Maximum Ice Accretion and Aerodynamic Performances of RG-15 Aerofoil at Low Reynolds Number

Cheng,

Zhao,

et al. 2023

Aerospace

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Ice accretion is inevitable on fix-wing UAVs (unmanned aerial vehicles) when they are applied to surveillance and mapping over colder climates and arctic regions. Subsequent aerodynamic profile changes have caused the current interest in the better prediction of the effect of icing shapes/sizes/distribution patterns on the aerodynamic performances of an aircraft. This study employs a numerical model which investigates the RG-15 aerofoil’s response to various icing scenarios at a Reynolds number of Re=2×105. Under icing conditions, compared to a clean aerofoil, a reduction in the lift coefficient and an increase in the drag coefficient are observed. Lower temperatures and reduced liquid water content lead to a decrease in the maximum thickness of ice accretion on the RG-15 aerofoil. Particularly noteworthy is the 10.85% reduction in the lift coefficient at a 10° angle of attack, which is in the icing condition at −10 °C with a mean volume diameter of 15 μm. Power consumption increases in the range of 0.46% to 26.5% under various icing conditions, showing synchronization with the rise in drag coefficient. This study underscores the need for future research to investigate various cloud conditions comprehensively and deeply in the context of aerofoil icing.

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UAV Icing: Numerical Simulation of Icing Effects on Wing and Empennage

Cited by 2 publications

References 14 publications

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Numerical Investigation on Intermittent Maximum Ice Accretion and Aerodynamic Performances of RG-15 Aerofoil at Low Reynolds Number

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