Design optimization of hot-air anti-icing systems by FENSAP-ICE

Pellissier, Mathieu; Habashi, Wagdi G.; Pueyo, Alberto

doi:10.2514/6.2010-1238

Cited by 15 publications

(6 citation statements)

References 34 publications

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“…Glaze icing is considered to be more dangerous since it usually leads to much more dramatic increases in drag and decreases in lift 3 . Although many efforts have been made in recent years [4][5][6][7][8][9][10][11] , aircraft icing remains an important unsolved problem that is threatening the aviation safety.…”

Section: Introductionmentioning

confidence: 99%

A Comparison Study on AC-DBD Plasma and Electrical Heating for Aircraft Icing Mitigation

Liu

Kolbakir

2018

2018 AIAA Aerospace Sciences Meeting

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A comparison study of utilizing thermal effects of a Dielectric-Barrier-Discharge (DBD) plasma actuator and a conventional electrical film heater for aircraft icing mitigation was performed in an Icing Research Tunnel available at Iowa State University (i.e., ISU -IRT). A NACA0012 airfoil/wing model embedded with an AC-DBD plasma actuator and a conventional electrical film heater over the airfoil surface was tested under a typical aircraft icing condition. While a high-speed imaging system was used to record the dynamic ice accretion and transient surface water transport processes over the airfoil surface, an infrared (IR) thermal imaging system was also utilized to map the corresponding surface temperature distributions over the airfoil surface simultaneously to quantify the unsteady heat transfer and phase changing process over the ice accreting airfoil surface. It was found that, for the same input power, the AC-DBD plasma actuator and the electrical film heater showed almost the equivalent effectiveness in preventing ice accretion over the airfoil surface. With the same total power input, further optimization of the AC-DBD plasma actuator with a duty-cycle modulation was found to have a better anti-/de-icing performance, in comparison to the conventional electrical film heater. The findings derived from the present study demonstrated the potential of a new class of anti-/de-icing strategy by leveraging the thermal effects of DBD plasma actuators for aircraft in-flight icing mitigation.

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Section: Introductionmentioning

confidence: 99%

A Comparison Study on AC-DBD Plasma and Electrical Heating for Aircraft Icing Mitigation

Liu

Kolbakir

2018

2018 AIAA Aerospace Sciences Meeting

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“…The goal was to create a numerical database for numerical correlations. Pellissier et al [71] studied the optimization of piccolo tubes using 3-d computational fluid dynamics, reduced order models (Proper Orthogonal Decomposition), and genetic algorithms to determine the optimal configuration (jet angles, spacing of holes, and position from leading edge). In this study, a Nusselt number correlation for heat transfer in the internal skin was calibrated using CFD data to reduce computational time and cost.…”

Section: Literature Reviewmentioning

confidence: 99%

Computational Methodology for Bleed Air Ice Protection System Parametric Analysis

Domingos

Papadakis

Zamora³

2010

AIAA Atmospheric and Space Environments Conference

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“…They concluded the etched surface or inner liner yields better surface heat transfer than the others so that such design patterns were favorable recommended. Pellissier et al [1] proposed a method to achieve the optimization of aircraft hot-air kind of anti-icing system. Their approach combined with 3D CFD, reduced order models and genetic algorithm was developed and optimal configuration of the PTS was offered by considering angles of jet, spacing between holes, and position from leading edge.…”

Section: Introductionmentioning

confidence: 99%

“…The ice is built up on the airplane surface and may alter the aerodynamic performance and stability of the aircraft leading to severe threat to flight safety [1][2][3]. Since the wing is one of aircraft key lifting-generated components, to avoid in-flight ice accretion and make the airplane flight safety, the thermal anti-icing system is widely used for ice prevention in the medium/large size of aircrafts.…”

Section: Introductionmentioning

confidence: 99%

Critical Design Points for the Wing Anti-Icing System

Zhu

Han

Hongliang

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The design parameters for the wing anti-icing system (WAIS) are determined with the flight conditions and atmospheric and meteorological conditions. To meet such a variety of conditions, the worst conditions are generally considered for the WAIS design. In this paper an approach is proposed to determine the design parameters for the WAIS, ie critical design points (CDP). In the framework of the Eulerian method, both of the air flow field and droplet impingement behavior are obtained by numerically solving two sets of Navier-Stokes equations. As the result, the heat flux requested for dry surface conditions is estimated, on the other hand, the heat flux supplied for icing prevention by the piccolo tube system (PTS) can be calculated based on the first law of thermodynamics. Then the distributions of connective heat transfer coefficients and droplet impinging mass flux along the wingspan are predicted.

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Design optimization of hot-air anti-icing systems by FENSAP-ICE

Cited by 15 publications

References 34 publications

A Comparison Study on AC-DBD Plasma and Electrical Heating for Aircraft Icing Mitigation

A Comparison Study on AC-DBD Plasma and Electrical Heating for Aircraft Icing Mitigation

Computational Methodology for Bleed Air Ice Protection System Parametric Analysis

Critical Design Points for the Wing Anti-Icing System

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