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In-Flight Icing Simulations on Airfoils

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Sustainable Aviation

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Abstract

It is crucial to predict the ice mass, shape and regions of the airframe which are prone to icing in order to design and develop de/anti-icing systems for aircraft and airworthiness certification . In the current study, droplet collection efficiency and ice shape predictions are performed using an originally developed computational tool for a wing tip for which experimental and numerical data are available. Ice accretion modeling consists of four steps in the developed computational tool: flow field solution, droplet trajectory and collection efficiency calculations, thermodynamic analyses and ice growth calculations using the Extended Messinger Model. The models used for these steps are implemented in a FORTRAN code, which is used to analyze ice accretion on 2D geometries including airfoils and axisymmetric inlets. The results are compared with numerical and experimental data available in the literature.

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Abbreviations

A p :

Droplet cross-sectional area, m2

b :

Span of wing, m

B :

Ice thickness, m

C D :

Droplet drag coefficient

C p :

Pressure coefficient

D :

Drag force, N

g :

Gravitational acceleration, ms−2

h :

Water layer thickness, m

HTC:

Convective heat transfer coefficient, W/m2.K

k :

Thermal conductivity, W/m.K

LWC:

Liquid Water Content, g/m3

L F :

Latent heat of solidification, J/kg

m :

Droplet mass, kg

\( \dot{m}_{\text{in}} \) :

Mass flow rate of runback water, kg/m2s

\( \dot{m}_{{\text{e}}, {\text{s}}} \) :

Mass flow rate of evaporating (or sublimating) runback water, kg/m2s

M :

Mach number

MVD:

Median Volume Diameter, μm

P :

Pressure (N/m2)

r :

Recovery factor

R :

Gas constant, J/kg.K

t :

Time, s

T :

Temperature, K

U e :

Boundary layer edge velocity, m/s

V x, V y :

Flow velocity components at the droplet location, m/s

V rel :

Relative velocity, m/s

V ∞ :

Freestream velocity, m/s

\( {\dot{\textit x}}, {\dot{\textit y}} \) :

Droplet velocity components, m/s

\( {\ddot{\textit x}},{\ddot{\textit y}} \) :

Droplet acceleration components, m/s2

y :

Spanwise distance from root, m

α:

Angle of attack

β:

Collection efficiency

γ:

Angle between droplet and flow velocity, Ratio of specific heats

ρ:

Ambient density (kg/m3)

θ:

Temperature in water layer, K

a:

Ambient

f:

Freezing

i:

Ice

s:

Substrate

static:

Static freestream conditions

w:

Water

References

  • Bidwell CS, Papadakis M (2005) Collection efficiency and ice accretion characteristics of two full scale and one ¼ scale business jet horizontal tails. NASA/TN-2005-213653

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  • European Aviation Safety Agency (EASA) (2015) Certification specifications for large aeroplanes CS-25

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  • Gent RW, Dart NP, Cansdale JT (2000) Aircraft icing. Phil Trans R Soc Lond A 358:2873–2911

    Article  MATH  Google Scholar 

  • Mason JG, Strapp JW, Chow P (2006) The ice particles threat to engines in flight, In: 44th AIAA aerospace sciences meeting and exhibit, Reno, AIAA 2006-206

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  • Myers TG (2001) Extension to the Messinger model for aircraft icing. AIAA J 39:211–218

    Article  Google Scholar 

  • Özgen S, Canıbek M (2009) Ice accretion simulation on multi-element airfoils using extended Messinger model. Heat Mass Transf 45(3):305–322

    Article  MATH  Google Scholar 

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Acknowledgements

This study is supported by the Ministry of Science, Industry and Technology of Turkey under the grant 0046.STZ.2013-1. The project partners are Middle East Technical University (METU) and TUSAŞ Engine Industries (TEI).

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Authors and Affiliations

  1. Middle East Technical University, Ankara, Turkey

    Nermin Uğur & Serkan Özgen

  2. TUSAŞ Engine Industries Inc., Eskişehir, Turkey

    İlhan Görgülü & Volkan Tatar

Authors
  1. Nermin Uğur
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  2. Serkan Özgen
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  3. İlhan Görgülü
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  4. Volkan Tatar
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Corresponding author

Correspondence to Serkan Özgen .

Editor information

Editors and Affiliations

  1. Anadolu Univeristy, Tepebaşı, Turkey

    T. Hikmet Karakoc

  2. Bahçeşehir University, Beşiktaş/İstanbul, Turkey

    M. Baris Ozerdem

  3. Anadolu Univeristy, Tepebaşı, Turkey

    M. Ziya Sogut

  4. Dokuz Eylul University, Alsancak, Izmir, Turkey

    Can Ozgur Colpan

  5. FACULTY OF AERONAUTICS AND ASTRONAU, Anadolu Univeristy, Tepebaşı, Turkey

    Onder Altuntas

  6. Bilecik S.E. University, Gulumbe, Bilecik, Turkey

    Emin Açıkkalp

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Uğur, N., Özgen, S., Görgülü, İ., Tatar, V. (2016). In-Flight Icing Simulations on Airfoils. In: Karakoc, T., Ozerdem, M., Sogut, M., Colpan, C., Altuntas, O., Açıkkalp, E. (eds) Sustainable Aviation. Springer, Cham. https://doi.org/10.1007/978-3-319-34181-1_22

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  • DOI: https://doi.org/10.1007/978-3-319-34181-1_22

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-34179-8

  • Online ISBN: 978-3-319-34181-1

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