In-Flight Icing Simulations on Airfoils

Date

2016-01-01

Author

Uğur, Nermin
Özgen, Serkan
Görgülü, İlhan
Tatar, Volkan

Metadata

Show full item record

Item Usage Stats

230
views

0
downloads

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 solution, droplet trajectory and collection efficiency calcu- lations, 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.

URI

https://hdl.handle.net/11511/82869

Relation

Sustainable Aviation, Energy and Environmental Issues

Collections

Department of Aerospace Engineering, Book / Book chapter

Suggestions

OpenMETU
Core

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...
In-flight Ice formation simulation on finite wings and air intakes Özgen, Serkan (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...
Static and Dynamic Aeroelastic Analysis of a Very Light Aircraft Demirer, Halime Gül; Kayran, Altan (2021-09-08) Aircraft design processes need to ensure that the aircraft will be aeroelastically stable within its operational envelope. This paper presents an overview of the static aeroelastic analysis results, flutter analysis and gust response analysis results of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. Aerodynamic calculations are based on the Doublet-Lattice Method (DLM), the aerodynamic theory employed by Nastran for subsonic flows. DLM requires all lif...
Experimental analysis of 3-D sweeping wings Çakır, Hasan; Kurtuluş, Dilek Funda; Department of Aerospace Engineering (2015) The aim of this thesis is to modify the mechanism, which is capable of mimicking the insect flight and developed previously by the Aerospace Engineering Department, and to measure the forces and moments of three types of flapping wings fixed to this mechanism. The flapping wing design is a new research topic, comparably young area and can be the future for micro unmanned air vehicles. Time varying force and moment data obtained from the experiments conducted in water as part of this thesis can be used to de...
Static and dynamic aeroelastic analysis of a very light Aircraft Demirer, Halime Gül; Kayran, Altan; Department of Aerospace Engineering (2021-9-10) Aircraft design processes need to ensure that the aircraft is aeroelastically stable within its operational envelope. This thesis presents an overview of the static aeroelastic, flutter and gust response analysis of a very light aircraft. MSC.FlightLoads and MSC.Nastran are used for aeroelastic modeling and analysis. The methods to be used in the aeroelastic analysis of the VLA are tested on the AGARD 445.6 wing, and the results are in good agreement with the literature. Aeroelastic model corrections such a...

Citation Formats

N. Uğur, S. Özgen, İ. Görgülü, and V. Tatar, In-Flight Icing Simulations on Airfoils. 2016, p. 289.