Numerical Method for Ice Accretion on 3D Wings

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Abstract

Computer simulations of the ice accretion process provide an attractive method for analyzing a wide range of icing conditions at low cost. An ice accretion model that accurately predicts ice growth shapes on arbitrary airfoils sections is valuable for the analysis of the sensitivity of airfoils for ice accretion. Furthermore the analysis of the influence of flow variables such as airspeed and angle of attack, pressure, temperature and humidity on ice accretion is studied easily. Such an approach can also be used to assess the energy requirements necessary to prevent and/or remove ice from an airfoil. Once the method has been validated, it will provide a cost-effective means of performing icing research studies which now rely, for an important part, on experimental techniques. In this paper, a computational method is presented that computes three dimensional ice accretion on multiple-element airfoils in specified icing conditions. The main part of the method is the method to compute the distribution of the supercooled water impinging on the wing surface, which is a challenge especially for so-called super-cooled large droplets (SLD). To this aim, for a given flow field solution, the numerical method ( Droplerian) uses an Eulerian method to determine the spatial distribution of the LiquidWater Content (LWC) and the droplet velocities. To solve the equations for the droplet velocities and liquid water content distribution, Droplerian uses a Finite Volume Method for unstructured grids. Through the droplet velocities and LiquidWater Content at the surface of the airfoil the droplet catching efficiency is calculated. The method can handle a multi-disperse droplet distribution with an arbitrary number of droplet classes (bins) and contains a droplet splashing and droplet rebound model. The splashing and rebound models are indispensable for correctly treating impingement of SLD's. Once the dropletcatching efficiency and droplet impact velocity are determined, they are used as input for the icing model, which is based on Messinger's model for ice accretion.
Original languageUndefined
Title of host publicationProceedings of 28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012)
EditorsI. Grant
Place of PublicationEdinburgh
Pages802-808
Number of pages7
ISBN (Electronic)9781622767540
Publication statusPublished - 23 Sep 2012
Event28th Congress of the International Council of the Aeronautical Sciences, ICAS 2012 - Brisbane, Australia
Duration: 23 Sep 201228 Sep 2012
Conference number: 28

Publication series

NameICAS Paper
Number2012-1.4.3

Conference

Conference28th Congress of the International Council of the Aeronautical Sciences, ICAS 2012
Abbreviated titleICAS
CountryAustralia
CityBrisbane
Period23/09/1228/09/12

Cite this

Hospers, J., & Hoeijmakers, H. W. M. (2012). Numerical Method for Ice Accretion on 3D Wings. In I. Grant (Ed.), Proceedings of 28th Congress of the International Council of the Aeronautical Sciences (ICAS 2012) (pp. 802-808). (ICAS Paper; No. 2012-1.4.3). Edinburgh.