Ice Accretion Effect on the Aerodynamic Characteristics of KC-100 Aircraft

Jung, Sung-Ki; Myong, R.S.; Jeong, Hyun–Cheol; Jung, J. H.

doi:10.2514/6.2010-1237

Cited by 8 publications

(3 citation statements)

References 11 publications

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“…It would be more natural to compute the droplet impingement on airfoils using an Eulerian approach rather than the Lagrangian model [8]. Furthermore the Eulerian approach is more flexible for three-dimensional complex geometries [5]. Despite improvements in the theoretical approaches and the use of computers, a whole computation considering flight and icing conditions under FAR 25 Appendix C [6] is still a computationally time-consuming problem.…”

Section: Introductionmentioning

confidence: 99%

An efficient CFD-based method for aircraft icing simulation using a reduced order model

et al. 2011

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In-flight icing is a critical technical issue for aircraft safety and, in particular, the droplet impingement areas on aircraft surfaces must be investigated for anti-/de-icing devices. As a step toward the prediction of droplet impingement on aircraft, an Eulerian-based droplet impingement code that provides collection efficiency for air flows around an airfoil containing water droplets is developed. A computational fluid dynamics (CFD) solver was also developed to solve the clean airflow. Then, a proper orthogonal decomposition (POD) method, a reduced order model (ROM), that optimally captures the energy content from a large multi-dimensional data set is utilized to efficiently predict the collection efficiency and ice accretion shapes on an airfoil following the mean volume diameter, liquid water contents and angle of attacks. As a result it is shown that the collection efficiency and ice shapes were in good agreement with the simulated and predicted results.

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Section: Introductionmentioning

confidence: 99%

An efficient CFD-based method for aircraft icing simulation using a reduced order model

et al. 2011

Self Cite

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“…Ice accumulation on the wings of aircraft can impact the mechanical components and aerodynamics, leading to catastrophic failure. − On December 8, 2014, a small aircraft crashed into a house in Gaithersburg, Maryland (six fatalities), the cause of which was ice buildup on the wings due to the ice protection system not being turned on . To reduce the risk of ice formation on aircraft wings, anti-icing liquids are sprayed on the aircraft before take-off. , These anti-icing liquids have been characterized to resist ice formation for a specified amount of time under specific conditions, known as the holdover time. , Additional safety considerations include requiring pilots to visually confirm that no ice has accumulated on the wings .…”

Section: Introductionmentioning

confidence: 99%

Modified Microwave Sensor with a Patterned Ground Heater for Detection and Prevention of Ice Accumulation

Kozak

Wiltshire

Khandoker

et al. 2020

ACS Appl. Mater. Interfaces

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Ice accumulation on aircraft is known to negatively impact the aerodynamic and mechanical operation, sometimes resulting in catastrophic failure. Recently, microwave resonators have gained interest as durable and reliable frost and ice detectors. Here, a microwave resonator sensor with built-in heating capability patterned into the ground plane was designed, fabricated, and tested to investigate real-time ice and frost growth. Sensing was performed on surfaces with anti-icing coatings to quantitatively analyze the effectiveness of these materials. The sensor was also tested to determine its ability to evaluate different deicing methods. The sensor itself was a split-ring resonator (SRR) operating at 5.82 GHz, which could effectively distinguish between water and ice by detecting changes in the dielectric properties on or around its surface. This application was particularly suited for an SRR due to the extreme difference between the relative permittivity of water (ε = 90) and ice (ε = 3.2) at 5 GHz and 0 °C. The results from this sensor can be used to determine the holdover time of various coatings to resist ice formation. This study validates the use of SRRs as ice detection sensors for applications where ice and frost are of great interest, such as on aircraft, roads, or walkways.

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“…In recent years, many departments in the world have been developing their own icing code or software, such as the National Aeronautics and Space Administration(NASA) in America, the Defence Research Agency(DRA) in British, the Office National d'Etudes et de Recherches Aerospatiales(ONERA) in France, and the Numerical Technologies International(NTI) in Canada [4][5][6] . All of the ice accretion codes at least consist of four modules for calculation of ice growth on a body subjected to icing conditions, these modules can generate the grid system for the geometry, calculate the flow field around the aircraft body, water droplet trajectories and impingement characteristics, analyses the mass and energy balance of water on the geometric surfaces.…”

Section: Introductionmentioning

confidence: 99%

Development and Validation of Aircraft Icing Computational Simulation Code

Zhu

Guo

et al. 2015

Proceedings of the 2nd International Conference on Intelligent Computing and Cognitive Informatics

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The purpose of this paper is to present some results on the development and verification of NUAA-ICE2D icing software code, which contains five separate program modules and a graphical user interface. Computational simulation of the ice accretion process on airfoils using multiple time-steps is studied in this paper. Firstly, all the modular codes for icing computation have been established in FORTRAN90 based on the Dynamic Link Library (DLL), and then a software package to perform normal functions of these modules has been developed using Microsoft Foundation Classes (MFC) framework. In addition, this icing software has some visualization tools that can help user analyze, explore and understand the simulation data. The architecture of the software, the functions of each component, its application to icing prediction and the further development are also discussed in this document. It is shown that all the modular codes of the software have good precision and fast calculation velocity during the process of grid generation, flow field calculation, droplet impingement calculation and ice growth analysis because of use of DLL and MFC, the illustration chart of operational interface is briefly shown in Figure 1. This platform software not only has established a reliable data communications law among these computational modules, but also has given an efficient way to predict the ice-layer accretion on the surfaces of geometry, the results are compared we are in accordance with the experimental data, shown in Figure 2. Once the calculations for ice accretion are activated, the software can call the five modules alternately and automatically in a robust way. This paper will provide some new techniques for predicting the ice accretion on airfoil efficiently and developing integrated icing software using mixed-language programming, which can be used in the stage of airfoil design and assessment. This paper presents some new ideas to improve the efficiency and reliability in icing calculations, especially in user-oriented way.

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Ice Accretion Effect on the Aerodynamic Characteristics of KC-100 Aircraft

Cited by 8 publications

References 11 publications

An efficient CFD-based method for aircraft icing simulation using a reduced order model

An efficient CFD-based method for aircraft icing simulation using a reduced order model

Modified Microwave Sensor with a Patterned Ground Heater for Detection and Prevention of Ice Accumulation

Development and Validation of Aircraft Icing Computational Simulation Code

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