In-flight Ice formation simulation on finite wings and air intakes

2012-04-01
In the present article, in-flight ice formation on finite wings and air intakes of low-speed aircraft are numerically studied. The approach to the problem involves calculation of the velocity field using a three-dimensional panel method. Using the calculated velocity field, the droplet trajectories and droplet impact locations are computed yielding the droplet collection efficiency distribution. In the next step, convective heat transfer coefficient distributions around the geometries are calculated using a two-dimensional Integral Boundary-Layer Method, which takes surface roughness due to ice accretion into account. A thermodynamic analysis employing the Extended Messinger Method yields the ice growth rates. Integration of these rates over time yields the ice shapes, hence the modified geometry. Predicted ice shapes are compared with experimental shapes reported in the literature and good agreement is observed. Ice shapes around vastly varying geometries including complex shapes are successfully computed. As such, the developed tool may be used for academical purposes or for airworthiness certification efforts.
AERONAUTICAL JOURNAL

Suggestions

In Flight Icing Simulations on Airfoils
Uğur, Nermin; Özgen, Serkan; Görgülü, İlhan; Tatar, Volkan (null; 2015-05-31)
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 solutio...
Search for Gluinos in Events with Two Same-Sign Leptons, Jets, and Missing Transverse Momentum with the ATLAS Detector in pp Collisions at root s=7 TeV
Aad, G.; et. al. (2012-06-15)
A search is presented for gluinos decaying via the supersymmetric partner of the top quark using events with two same-sign leptons, jets, and missing transverse momentum. The analysis is performed with 2: 05 fb(-1) of integrated luminosity from pp collisions at root s = 7 TeV collected by the ATLAS detector at the LHC. No excess beyond the standard model expectation is observed, and exclusion limits are derived for simplified models where the gluino decays via the supersymmetric partner of the top quark and...
A new method to determine dynamically equivalent finite element models of aircraft structures from modal test data
Karaağaçlı, Taylan; Yıldız, Erdinç N.; Özgüven, Hasan Nevzat (Elsevier BV, 2012-8)
Flutter analysis is a major requirement to predict safe flight envelops and to decide on flutter testing conditions of newly designed or modified aircraft structures. In order to achieve reliable flutter analysis of an aircraft structure, it is necessary to obtain a good correlation between its finite element (FE) model and experimental modal data. Currently available model updating methods require construction of a detailed initial FE model in order to achieve convergence of the modes obtained from updated...
Design of an LPV Based Fractional Controller for the Vibration Suppression of a Smart Beam
Onat, Cem; Şahin, Melin; Yaman, Yavuz; Eswar, Prasad; Saılu, Nemana (2011-12-01)
One of the major problems encountered in the active vibration control of aircraft wings is the changing mass due to the in-flight fuel consumption. In this study, a Linear Parameter Varying (LPV) based fractional controller is designed for the suppression of the flexural vibrations of a smart beam. The designed controller is sensitive to the varying mass properties. The smart beam studied was a cantilever aluminium beam with eight surface bonded Lead-Zirconate-Titanate (PZT) patches. The smart beam was exci...
In-Flight Icing Simulations on Airfoils
Uğur, Nermin; Özgen, Serkan; Görgülü, İlhan; Tatar, Volkan (Springer, 2016-01-01)
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 certificatlon. İn the current study, droplet collection efticiency 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 accretilon modeling consists of four steps in the developed compu- tational tool: flow field solu...
Citation Formats
S. Özgen, “In-flight Ice formation simulation on finite wings and air intakes,” AERONAUTICAL JOURNAL, pp. 337–362, 2012, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/55957.