Numerical and Experimental Investigation of Ice Accretion on Rotorcraft Engine Air Intake

Ice accretion on the surface of an electrothermal anti-icing system around a rotorcraft engine air intake was investigated on the basis of computational and experimental methods. A compressible Navier–Stokes–Fourier computational fluid dynamics code was used to determine the fully three-dimensional...

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Published in:Journal of aircraft 2015-05, Vol.52 (3), p.903-909
Main Authors: Ahn, G. B, Jung, K. Y, Myong, R. S, Shin, H. B, Habashi, W. G
Format: Article
Language:English
Subjects:
Aerodynamics
Aerospace engineering
Aerospace engines
Air intakes
Aircraft
Aircraft components
Airplane engines
Compressibility
Computation
Computational fluid dynamics
Deicing
Droplets
Efficiency
Fluid dynamics
Heat
Ice
Ice accumulation
Ice formation
Icing wind tunnels
Mathematical analysis
Numerical analysis
Partial differential equations
R&D
Research & development
Research methodology
Reynolds number
Rotary wing aircraft
Shear stress
Simulation
Three dimensional
Three dimensional flow
Trajectory control
Velocity
Viscosity
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cited_by cdi_FETCH-LOGICAL-a389t-b6408d6ce0d700af223c6d9308358299eec278276cbe2f9b26ae63bd329ddc683
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description Ice accretion on the surface of an electrothermal anti-icing system around a rotorcraft engine air intake was investigated on the basis of computational and experimental methods. A compressible Navier–Stokes–Fourier computational fluid dynamics code was used to determine the fully three-dimensional flowfield around the inlet of the engine and the environment control system. Three-dimensional droplet trajectory and ice accretion codes based on the Eulerian approach, DROP3D and ICE3D modules of FENSAP-ICE, were used to calculate the collection efficiency and ice shape on the surface of an engine air intake. Furthermore, an experimental study using an icing wind tunnel was conducted to validate the computational predictions of ice accretion on the surface of the electrothermal anti-icing system in heat-off and heat-on modes. It is shown that the general shape and range of ice accretion obtained by numerical calculations are in close agreement with experimental observation. In particular, two features of glaze ice formation identified from computational results, the upper parts of the intake with the largest ice accretion and the narrow region between these parts showing relatively small ice accumulation, were confirmed in the experimental study.
doi_str_mv 10.2514/1.C032839
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Furthermore, an experimental study using an icing wind tunnel was conducted to validate the computational predictions of ice accretion on the surface of the electrothermal anti-icing system in heat-off and heat-on modes. It is shown that the general shape and range of ice accretion obtained by numerical calculations are in close agreement with experimental observation. 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source Alma/SFX Local Collection
subjects Aerodynamics
Aerospace engineering
Aerospace engines
Air intakes
Aircraft
Aircraft components
Airplane engines
Compressibility
Computation
Computational fluid dynamics
Deicing
Droplets
Efficiency
Fluid dynamics
Heat
Ice
Ice accumulation
Ice formation
Icing wind tunnels
Mathematical analysis
Numerical analysis
Partial differential equations
R&D
Research & development
Research methodology
Reynolds number
Rotary wing aircraft
Shear stress
Simulation
Three dimensional
Three dimensional flow
Trajectory control
Velocity
Viscosity
title Numerical and Experimental Investigation of Ice Accretion on Rotorcraft Engine Air Intake
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