• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.11
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• pp.1094-1104
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• 2010

In the previous studies, the validation of numerical codes has been conducted based on the qualitative comparison of predicted ice shapes with experiments, which poses a significant limit on the systematic analysis of ice shapes due to the variation of meteorological conditions. In response to this, the numerical code has been quantitatively validated against available experiment for the ice accretion on cylinders and airfoils in the present study. Ice shapes accumulated on the bodies are systematically investigated with respect to various icing parameters. To this end, maximum thickness, heading direction and ice thickness are quantified and expressed in the polar coordinate system for the comparison with other numerical results. By applying the quantitative analysis, similar shapes are intuitively distinguished. The developed numerical code underestimates the ice accretion area and the ice thickness of lower surface. In order to improve the accuracy, further accurate aerodynamic solver is required for the water droplet trajectories.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.3
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• pp.147-155
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• 2022

The accumulated ice and snow during the operation of aircraft and railway vehicles can degrade aerodynamic performance or damage the major components of vehicles. Therefore, it is crucial to predict the temporal growth of ice for operational safety. Numerical simulation of ice is widely used owing to the fact that it is economically cheaper and free from similarity problems compared to experimental methods. However, numerical simulation of ice generally divides the analysis into multi-step and assumes the quasi-steady assumption that considers every time step as steady state. Although this method enables efficient analysis, it has a disadvantage in that it cannot track continuous ice evolution. The purpose of this study is to construct a surrogate model that can predict the temporal evolution of ice shape using reduced-order modeling. Reduced-order modeling technique was validated for various ice shape generated under 100 different icing conditions, and the effect of the number of training data and the icing conditions on the prediction error of model was analyzed.

• Journal of the Korean Society for Railway
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• v.14 no.3
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• pp.240-247
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• 2011

Finite element analysis was undertaken to investigate the effect of freezing force of water unexpectedly penetrated into inserts used in railway sleeper on pullout capacity of anchor bolts for fixing base-plate onto concrete sleeper. Based on the in-situ investigation and measurement of geometry of railway sleeper and rail-fastener, the railway sleeper was modeled by 3D solid elements. Nonlinear and fracture properties for the finite element model were assumed according to CEB-FIP 1990 model code. And the pullout maximum load of anchor bolt obtained from the model developed was compared with experimental pullout maximum load presented by KRRI for verification of the model. Using this model, the effect of position of anchor bolt, amount of fastening force applied to the anchor bolt, and compressive strength of concrete on pull-out capacity of anchor bolts installed in railway sleeper was investigated. As a result, it is found that concrete railway sleepers could be damaged by the pressure due to freezing of water penetrated into inserts. And the pullout capacity of anchor bolt close to center of railway is slightly greater than that of the others.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.40 no.8
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• pp.495-501
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• 2016

The measurement of icing conditions needs to be carried out accurately by the ice detector system of an aircraft. Ice detector systems should be installed in locations not affected by backwash, rotor downwash or moving doors or other equipment. Various analyses were carried out in order to find the proper locations sufficiently far from these interfering effects. In this study, the optimum position of the ice detector was assessed using computer simulation, with respect to different flight modes, flow velocities and the amount and distribution of liquid water around the sensor.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.526-532
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• 2015

In order to relieve limitation of flight operation under icing condition and verify its operation in adverse weather condition for Surion, military helicopter developed in Korea, airworthiness certification in icing condition is required. The process of Surion icing certification should be considered by implementation of four methods by step such as CFD analysis, simulated flight tests, artificial icing flight tests, and natural icing flight tests. For Surion icing flight tests, these are required 20~30 sorties and 20~23 hours in artificial icing condition; 20~30 sorties and 20~22 hours in natural icing condition. In addition, to proceed with efficient flight tests, it is necessary to implement artificial icing flight tests in LWC $0.5{\sim}1.0g/m^3;$ natural icing flight tests in less than LWC $0.5g/m^3$.

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.456-459
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• 2010

Icing is one of the most serious hazards for aircraft. The amount and rate of icing depend on a number of meteorogical and aerodynamic factors. Of primary importance are amount of liquid water content of droplets, their size, the temperature of aircraft surfaces, the collection efficiency, and the extent of supercooled droplets. In this study, in-flight icing analysis of low reynolds number high aspect ratio wing is carried out by using FENSAP-ICE. Each liquid water contents with altitude is obtained from FAR 25 Appendix-C. And the collectoin efficiency is calculated to check out the ice accretion position of wing with two angles of attack. The degradation of aerodynamic characteristics of aircraft are figured out by investigating the accretion of rime and glaze ice.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.6
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• pp.530-536
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• 2010

In-flight icing is a critical technical issue for aircraft safety and, in particular, ice accretions on aircraft surfaces can drastically impair aerodynamic performances and control authority. In order to investigate icing effects on the aerodynamic characteristics of KC-100 aircraft, a state-of-the-art CFD code, FENSAP-ICE, was used. A main wing section and full configuration of KC-100 aircraft were considered for the icing analysis. Also, shapes of iced area were calculated for the design of anti-/de-icing devices. The iced areas around leading edge of main wing and horizontal tail wing were observed maximum 7.07% and 11.2% of the chord length of wing section, respectively. In case of wind shield, 16.7% of its area turned out to be covered by ice. The lift of KC-100 aircraft were decreased to 64.3%, while the drag was increased to 55.2%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.4
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• pp.253-260
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• 2013

Ice accretions on the surface around a rotorcraft air intake can deteriorate the safety of rotorcraft due to the engine performance degradation. The computational simulation based on modern CFD methods can be considered extremely valuable in analyzing icing effects before exact but very expensive icing wind tunnel or in-flight tests are conducted. In this study the range and amount of ice on the surface of anti-icing equipment are investigated for heat-on and heat-off modes. It is demonstrated through the computational prediction and the icing wind tunnel test that the maximum mass and height of ice of heat-on mode are reduced about 80% in comparison with those of heat-off mode.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.1
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• pp.23-33
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• 2020

In this study, the effect of surface roughness distribution and its influence on the inflight icing code was investigated. Previous numerical studies focused on the magnitude of surface roughness, and the effects were only addressed in terms of changes in thermal boundary layers with fully turbulent assumption. In addition, the empirical formula was used to take account the turbulent transition due to surface roughness, which was regarded as reducing the accuracy of ice shape prediction. Therefore, in this study, the turbulent transition model based on the two-equation turbulence model was applied to consider the effects of surface roughness. In order to consider the effect of surface roughness, the transport equation for roughness amplification parameter was applied, and the surface roughness distribution model was implemented to consider the physical properties. For validation, the surface roughness, convective heat transfer coefficient, and ice shape were compared with experimental results and other numerical methodology. As a result, it was confirmed that the excessive prediction of the heat transfer coefficient at the leading edge and the ice horn shape at the bottom of the airfoil were improved accordingly.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.7
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• pp.445-454
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• 2022

Ice accretion on the aircraft components, such as wings, fuselage, and empennage, can occur when the aircraft encounters a cloud zone with high humidity and low temperature. The prevention of ice accretion is important because it causes a decrease in the aerodynamic performance and flight stability, thus leading to fatal safety problems. In this study, a shape design optimization of a multi-element airfoil is performed to minimize the amount of ice accretion on the high-lift device including leading-edge slat, main element, and trailing-edge flap. The design optimization framework proposed in this paper consists of four major parts: air flow, droplet impingement and ice accretion simulations and gradient-free optimization algorithm. Reynolds-averaged Navier-Stokes (RANS) simulation is used to predict the aerodynamic performance and flow field around the multi-element airfoil at the angle of attack 8°. Droplet impingement and ice accretion simulations are conducted using the multi-physics computational analysis tool. The objective function is to minimize the total mass of ice accretion and the design variables are the deflection angle, gap, and overhang of the flap and slat. Kriging surrogate model is used to construct the response surface, providing rapid approximations of time-consuming function evaluation, and genetic algorithm is employed to find the optimal solution. As a result of optimization, the total mass of ice accretion on the optimized multielement airfoil is reduced by about 8% compared to the baseline configuration.