A three-dimensional mathematical model for simulating ice accretion on helicopter rotors

Chen, Ningli; Ji, Honghu; Cao, Guangzhou; Hu, Yaping

doi:10.1063/1.5041896

Cited by 20 publications

(6 citation statements)

References 15 publications

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“…For example, the application of natural laminar flow technique requires the extremely smooth and precisely finished surfaces, while the current mechanical-based and hot-air anti/de-icing techniques have surface gaps and steps configurations which can provoke laminar-turbulent transition. 9 Moreover, recently various mathematical and numerical models have been proposed to simulate the ice accretion over the three dimensional surfaces and rotors 10,11 to help in development of novel icing control methods.…”

Section: Introductionmentioning

confidence: 99%

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Meng

et al. 2019

Physics of Fluids

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Anti-icing performance using the surface dielectric barrier discharge plasma actuator is studied using detailed visualization and surface thermal measurements. To reveal the physical mechanism of coupled aerodynamic and thermal effects on anti-icing, three types of actuators are designed and mounted on a NACA 0012 airfoil. The coupled aerodynamic and thermal effects are confirmed in still air. The results show that the plasma actuation is effective for in-flight anti-icing, and the anti-icing performance is directly related to the design of the plasma actuators based on the coupled aerodynamic and thermal effects. When the direction of plasma induced flow is consistent with the incoming flow, the heat generated by plasma discharge is concentrated in the region of the actuator and the ability of the actuator for heat transfer downstream is relatively weak during the anti-icing. When the induced flow is opposite to the incoming flow, there is less heat accumulation in the actuator region, while the ability of heat transfer downstream becomes stronger. With the consistent and opposite direction of induced flow, the plasma actuation can ensure that 57% and 81% chord of the lower surface of the airfoil are free of the ice accumulation, respectively. Another actuator is designed to induce the air jets approximately perpendicular to the airfoil surface. This exhibits both a stronger ability of heat accumulation locally and heat transfer downstream and hence ensures that there is no ice on the entire lower surface of the airfoil.

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Section: Introductionmentioning

confidence: 99%

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Meng

et al. 2019

Physics of Fluids

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“…As a result, besides the first and second fundamental metric tensors, second cross fundamental forms of the surface were included to address the influence of the metrics. Similarly, to simulate the ice accretion on helicopter rotors, Chen 12 developed a three-dimensional ice accretion model on body-fitted nonorthogonal curvilinear coordinates. In this model, besides the gravity force, the centrifugal caused by the rotation of the coordinate was also accounted as body force.…”

Section: Introductionmentioning

confidence: 99%

Finite volume based film flow and ice accretion models on aircraft wings

Liu¹,

Cai²,

Qu³

et al. 2022

Preprint

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The thin runback water films driven by the gas flow, the pressure gradient and the gravity on the iced aircraft surface are investigated in this paper. A three-dimensional film flow model based on Finite Volume Method (FVM) and the lubrication theory is proposed to describe the flow. The depth-averaged velocity of the film is stored in Cartesian coordinates to avoid the appearance of the metric tensors. The governing equations are discretized in the first layer structured grid cell which is selected as the grids for film flow. In order to verify this method, comparisons between numerical results and experimental results of ice shapes on NACA 0012 airfoil and GLC-305 swept wing are presented, both showing a good agreement for rime and glaze ice condition. Overall, this model shows great potential to model ice accretion reasonably under different icing conditions. Besides, the present method doesn't require analytic metric terms, and can be easily coupled to existing finite volume solvers for logically Cartesian meshes.

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“…16 Three-dimensional numerical investigations have been conducted on rotor icing simulations in both hovering and forward flight these years. [17][18][19][20][21][22] It is noted that direct simulation of the complex ice accretion process on the three-dimensional rotor is time-consuming. Additionally, ice accretion involves multidisciplines, such as aerodynamics, kinematics, and thermodynamics.…”

Section: Introductionmentioning

confidence: 99%

Experimental investigation on the performance degradation of helicopter rotor due to ice accretion

Huang

Yuan

Wang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part G:

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Helicopter rotor performance can be significantly altered by ice accretion which directly degrades the handling qualities and safety during flight. To obtain understanding into the effect of ice accretion on a helicopter rotor in forward flight under different icing environments, an experimental campaign was conducted in an icing wind tunnel using a rotor model with diameter at 2 m. Research was emphasized on revealing effect of liquid water content and static temperature on the rotor performance degradation. The dynamic thrust and torque of the rotor were measured by a six-component balance. Ice shape of the airfoils at specific rotor blade spanwise locations was obtained through the ice cutting process; meanwhile, the entire ice topology on the blade was scanned by means of the three-dimensional scanning technique. Results showed that ice was mainly accreted on the leading edge and lower surface of the blade. The static temperature of a icing cloud has a noticeable effect on the regime of accreted ice. The ice formation was transparent glaze at −8°C and transformed to milky rime when changed the static temperature to −20°C. Comparing to rime ice, the glaze ice on the blade is more influential to the rotor performance degradation. Particular attention is given to the fact that under extreme icing conditions, over 30% degradation of transient rotor thrust was observed.

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A three-dimensional mathematical model for simulating ice accretion on helicopter rotors

Cited by 20 publications

References 15 publications

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Mechanism study of coupled aerodynamic and thermal effects using plasma actuation for anti-icing

Finite volume based film flow and ice accretion models on aircraft wings

Experimental investigation on the performance degradation of helicopter rotor due to ice accretion

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