Experimental Investigation on the Dynamic Icing Process over a Rotating Propeller Model

Liu, Yang; Li, Linkai; Ning, Z.; Tian, Wei; Hu, Hui

doi:10.2514/1.b36748

Cited by 35 publications

(52 citation statements)

References 33 publications

(49 reference statements)

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“…In summary, ISU-IRT can be used to simulate atmospheric icing phenomena over a range of icing conditions (i.e. from dry rime to extremely wet glaze ice conditions) [41,42].…”

Section: Experimental Setup and Test Modelmentioning

confidence: 99%

“…U ∞ = 40 m s −1 and LWC=1.0 g m −3 , three typical ice accretion processes (i.e. rime, mixed, and glaze icing [42]) were tested on the actuator-embedded-airfoil/wing model by changing the airflow temperature from −15°C to −5°C, with the operating frequency of the NS-DBD plasma actuators being varied from f=2 to 6 kHz.…”

Section: Application Of Ns-dbd Plasma Actuation For Aircraft Icing MImentioning

confidence: 99%

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An experimental study on the thermal characteristics of NS-DBD plasma actuation and application for aircraft icing mitigation

Liu

Kolbakir

Starikovskiy

et al. 2019

Plasma Sources Sci. Technol.

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A comprehensive study was performed to explore the thermal characteristics of NS-dielectric-barrier discharge (DBD) plasma actuation over an airfoil/wing surface and evaluate the anti-/de-icing performance of NS-DBD plasma actuators for aircraft in-flight icing mitigation. While the fundamentals of thermal energy generation and heat transfer in NS-DBD plasma actuation over the airfoil/wing model were described in great details, a series of experiments were conducted to evaluate the effects of different environmental parameters on the heating efficiency of NS-DBD plasma actuators over the airfoil/wing surface. With the temporally-synchronized-and-spatiallyresolved high-speed visualization and infrared imaging system, not only the transient thermal characteristics of NS-DBD plasma actuation over the airfoil/wing surface were revealed, but also the anti-icing performances of the NS-DBD plasma actuators were evaluated under different icing conditions, i.e. rime, mixed, and glaze. The impacts of incoming airflow velocity, air temperature, and angle of attack of the airfoil/wing model on the thermal characteristics of NS-DBD plasma actuation over the airfoil/wing surface were systematically investigated based on the measurement results. It was found that the thermal characteristics of NS-DBD plasma actuation over the airfoil/ wing surface are closely coupled with the boundary layer airflow and the unsteady heat transfer process over the airfoil/wing model exposed in the frozen-cold airflows. The anti-icing performances of the NS-DBD plasma actuators under the different icing conditions were found to be varying significantly due to the variations of surface heating efficiency of the NS-DBD plasma actuators. The anti-/de-icing performance of the NS-DBD plasma actuators was found to be improved dramatically by increasing the operating frequency of the plasma actuators. The findings derived from the present study are very helpful to explore/optimize design paradigms for the development of novel plasma-based anti-/de-icing strategies tailored specifically for aircraft inflight icing mitigation to ensure safer and more efficient aircraft operation in atmospheric icing conditions.

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“…In summary, ISU-IRT can be used to simulate atmospheric icing phenomena over a range of icing conditions (i.e. from dry rime to extremely wet glaze ice conditions) [41,42].…”

Section: Experimental Setup and Test Modelmentioning

confidence: 99%

Section: Application Of Ns-dbd Plasma Actuation For Aircraft Icing MImentioning

confidence: 99%

An experimental study on the thermal characteristics of NS-DBD plasma actuation and application for aircraft icing mitigation

Liu

Kolbakir

Starikovskiy

et al. 2019

Plasma Sources Sci. Technol.

Self Cite

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“…In comparison to that over the surfaces of the fixed UAS wings, the dynamic ice accretion process over the rotating propeller blades was found to be more complicated, due to the combined effects of aerodynamics forces and centrifugal forces, caused by the rotational motion of the UAS propellers. As revealed in Liu et al [10], the ice accretion over a rotating propeller is more preferable along the radial direction, which is similar to that on wind turbine rotor blades [20][21][22]. It was also found that the ice accretion on UAS propellers, particularly in glaze icing conditions, can cause a significant reduction in thrust generation and a dramatic increase in loading fluctuating magnitude [10].…”

Section: Introductionmentioning

confidence: 73%

“…Due to the wet nature of glaze ice that involves complex multiphase mass and heat transfer, the formation and growth of glaze ice are more difficult to predict, due to the generation of irregular "horns" and larger "feathers" growing outward into the airflow [9]. Such large ice features were suggested to have a severe effect on the flight performance of UAS by causing large scale flow separations and unexpected structural unbalance [10].…”

Section: Introductionmentioning

confidence: 99%

“…Thus, when a UAS encounters an icing event, ice may accumulate not only on the fixed UAS wings, but also on the rotating blades of the UAS propeller, which can significantly degrade the flight performance of UAS due to the aerodynamic penalties of the iced propeller. However, while most of the previous studies have focused on the description of ice accretion and development of anti-/de-icing strategies on UAS wings [17,18], the dynamic ice accretion process on UAS propellers was not investigated until the recent experimental studies of Liu et al [10,19]. In comparison to that over the surfaces of the fixed UAS wings, the dynamic ice accretion process over the rotating propeller blades was found to be more complicated, due to the combined effects of aerodynamics forces and centrifugal forces, caused by the rotational motion of the UAS propellers.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Liu

2018

2018 Atmospheric and Space Environments Conference

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A comprehensive experimental study was performed to investigate the effects of ice accretion on the aerodynamic performances and wake characteristics of a UAS propeller model under different icing conditions (i.e., rime vs. glaze). The experimental study was conducted in the unique Icing Research Tunnel available at Iowa State University (ISU-IRT). In addition to acquiring the key features of ice accretion on the rotating propeller blade using a "phase-locked" imaging technique, the wake characteristics of the rotating UAS propeller under the different icing conditions were also resolved by using the Particle Imaging Velocimetry (PIV) technique along with the time-resolved measurements of aerodynamic forces and power consumption of the UAS propeller model. Both "free-run" and "phaselocked" PIV measurements were performed on the propeller model at different stages of the icing experiments (i.e., before, during and after the dynamic icing processes) to provide both the instantaneous flow characteristics and the ensemble-averaged flow statistics (e.g., mean velocity, vorticity, and turbulence kinetic energy) in the wake of the rotating propeller model. It was found that while the rime ice accretion would closely follow the original profiles of the propeller blades, the glaze ice was formed into very irregular structures (e.g., "lobster-taillike" ice structures) that can significantly disturb the wake flow field of the rotating propeller model, generating the much larger and more complex vortices. Such complex large-scale vortices were found to enhance the turbulent mixing in the propeller wake and produce an evident velocity deficit channel around the outer board of the propeller blades, which provided direct evidences in elucidating the dramatic decrease in thrust generation and the significant increase in power consumption of the rotating propeller model in icing conditions. The findings derived from this study revealed the underlying mechanisms of the aerodynamic performance degradation of the iced UAS propeller, which is of significant importance for the development of innovative, effective anti-/de-icing strategies tailored for UAS icing mitigation and protection to ensure the safer and more efficient UAS operations in atmospheric icing conditions.

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Applying an Icing Wind Tunnel for Drone Propeller Research, Validation of New Measurement Instrument

Suurnäkki

Jokela

Tiihonen

2021

New Developments and Environmental Applications of Drones

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Experimental Investigation on the Dynamic Icing Process over a Rotating Propeller Model

Cited by 35 publications

References 33 publications

An experimental study on the thermal characteristics of NS-DBD plasma actuation and application for aircraft icing mitigation

An experimental study on the thermal characteristics of NS-DBD plasma actuation and application for aircraft icing mitigation

Effects of Ice Accretion on the Aerodynamic Performance and Wake Characteristics of an UAS Propeller Model

Applying an Icing Wind Tunnel for Drone Propeller Research, Validation of New Measurement Instrument

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