Influence of multidroplet size distribution on icing collection efficiency

Chang, Ho-Pen; Kimble, K. R.; Frost, W.; Shaw, R. J.

doi:10.2514/6.1983-110

Cited by 3 publications

(2 citation statements)

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“…To simplify icing simulations, the droplets are normally assumed to be monodisperse although it has been shown that using droplet size distributions can improve the agreement with experimental results [28]. Since the simulation of intercycle ice shapes on UAVs with a parting strip is a novel method, it was also investigated whether the difference between monodisperse droplet sizes and the Langmuir-D droplet size distribution [29] was significant.…”

Section: Validation Of the Numerical Methodsmentioning

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: Validation Of the Numerical Methodsmentioning

confidence: 99%

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Wallisch¹,

Hann²

2023

SAE Technical Paper Series

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“…The value of the impinging water mass depends on the local collection efficiency β(x). Using a Lagrangian perspective, the local collection efficiency is calculated integrating trajectories of a droplet population distribution (Chang et al [25]). The local collection efficiency was calculated with Equation ( 23) and the droplets' trajectories were integrated according to the equations of reference Zarling [26] and using a Euler method.…”

Section: Convective Heat Transfer Coefficientmentioning

confidence: 99%

Icing Condition Predictions Using FBGS

Val

Mora

Gallego

et al. 2021

Sensors

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Icing is a hazard which is important for the aerospace industry and which has grown over the last few years. Developing sensors that can detect the existence not only of standard icing conditions with typically small droplet size, but also of Supercooled Large Droplet (SLD) conditions is one of the most important aims in order to minimize icing hazards in the near future. In the present paper a study of the Fiber Bragg Grating Sensors’ (FBGSs) performance as a flight icing detection system that predicts the conditions of an icing cloud is carried out. The test matrix was performed in the INTA Icing Wind Tunnel (IWT) with several icing conditions including SLD. Two optic fibers with 16 FBGS in total were integrated in the lower and upper surface of an airfoil to measure the temperature all over the chord. The results are compared with a Messinger heat and mass balance model and the measurements of the FBGS are used to predict the Liquid Water Content (LWC) and Ice Accretion Rate (IAR). Finally, the results are evaluated and a sensor assessment is made. A good correlation was observed between theoretical calculations and test results obtained with the FBGS in the IWT tests. FBGS proved to detect the beginning and end of ice accretion, LWC and IAR quickly and with good precision.

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Wind Tunnel Test of the Icing Characteristics of Airfoil Rotating around a Vertical Axis

Shi

Guo

et al. 2020

International Journal of Rotating Machinery

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To determine the process of icing on the rotating machinery, an icing experiment on a rotating airfoil blade was carried out in this paper. First, an icing wind tunnel was fabricated, and its conditional parameters were calibrated. The calibration results showed that the performance of this icing wind tunnel was reliable and stable. The experimental temperature was -15°C, and the MVD was 50 μm. Then, an icing experiment on the rotating blade with the NACA0018 airfoil was carried out. The characteristics of icing, including icing distribution, growth rate of icing, and thickness of the ice layer, were defined and quantitatively analyzed under different tip speed ratios and setting angles. The results show that the type of icing changes from rime ice to glaze ice with an increase in the tip speed ratio. The dimensionless icing area and dimensionless thickness of the ice layer both increase with an increase in the icing time. The growth rate of icing increases rapidly at the initial icing stage and then decreases dramatically under each tip speed ratio condition.

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Influence of multidroplet size distribution on icing collection efficiency

Cited by 3 publications

References 0 publications

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

UAV Icing: Intercycle Ice Effects on Aerodynamic Performance

Icing Condition Predictions Using FBGS

Wind Tunnel Test of the Icing Characteristics of Airfoil Rotating around a Vertical Axis

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