• JSTS:Journal of Semiconductor Technology and Science
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• v.10 no.4
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• pp.251-259
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• 2010

We proposed a tail function parameter extraction procedure for the establishment of a robust ion implantation database. We showed that, for the expression of ion implantation profiles, there are many local minimum values set for the third and fourth moment parameters of $\gamma$ and $\beta$ for the Pearson function that comprises the standard dual Pearson and tail functions. We proposed the use of a joined tail function as a mediate function to extract $\gamma$ and $\beta$, and demonstrated that this enables us to extract the parameters uniquely. Other parameters associated with channeling phenomena can also be simply and uniquely extracted by our procedure.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.16 no.12 s.117
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• pp.1238-1243
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• 2006

In a wheel loader, the tail-pipe is installed at the exhaust tube of muffler for the reduction of exhaust noise and the cooling of engine room, however, the cabin noise level can be largely increased due to the tail-pipe. In this paper, to grasp and reduce the cabin noise, a series of noise and vibration tests were carried out in addition to numerical simulations. As a result, the transmission path of exhaust noise toward the cabin was exactly identified and the improved shape of tail pipe, that can reduce the cabin noise, was derived through various numerical simulations and real tests.

• 한국전산유체공학회:학술대회논문집
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• 2007.10a
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• pp.149-156
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• 2007

A three-dimensional inviscid flow solver has been developed based on unstructured meshes for the simulation of steady and unsteady flowfields around a generic fighter aircraft and for the investigation of the aerodynamic interference between the external stores and the tail surfaces. The flow solver is based on a vertex-centered finite-volume method and an implicit point Gauss-Seidel relaxation scheme. To validate the flow solver, calculations were made for a steady flow and the computed results were compared with experimental data. An unsteady time-accurate computation of the generic fighter aircraft with external stores at transonic flight conditions showed that the external stores cause undesirable vibration on the horizontal tail surface due to the mutual interference between their wake and the horizontal tail surface. It was shown that downward deflection of the trailing edge flap significantly reduces the undesirable interference effect.

• The Bulletin of The Korean Astronomical Society
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• v.43 no.1
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• pp.72.3-72.3
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• 2018

Since there are two-different observational constraints for the lunar exosphere data, it is interesting to find the best exospheric model that can account for the observed characteristics of the lunar coma and tail simultaneously (Lee & Kim, 2017).The characteristics of the lunar exosphere can be constrained by comparing simulated models with observational data of the coma and tail. In this work, considering effects of triple sodium sources (two dayside sources: a low- and a high-velocity component; and an Isotropic source component), we present time-dependent simulations showing initial conditions around the lunar coma and the final stage of the lunar tail. Based on an updated 3-D lunar exosphere model (Lee & Kim, 2017), we are presenting the simulated images of the lunar sodium coma and its correlation with lunar tail's physical parameters.

• Journal of the Korean Institute of Telematics and Electronics A
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• v.32A no.3
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• pp.100-109
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• 1995

A new Hydrodynamic model for the high energy tail electrons(Tail Electron Hydrodynamic Model : TEHD) is developed using the moment method. The Monte Carlo method is applied to a $n^{+}-n^{-}-n^{+}$ device to calibrate the TEHD equations. the discretization method and numerical procedures are explained. New models for the impact ionization and injection into the gate oxide using the tail electron density are proposed. The simulated results of the impact ionization rate for a $n^{+}-n^{-}-n^{+}$ device and MOSFET devices, and the gate injection experiment are shown to give good agreement with the Monte Carlo simulation and the measurements.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.46 no.2
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• pp.47-51
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• 2009

The low latency encoder for high data rate duo-binary turbo codes with tail biting trellises is considered. Encoder hardware architecture is proposed using inherent encoding property of duo-binary turbo codes. And we showed that half of execution time as well as the energy can be reduced with the proposed architecture.

• Journal of the Korean Mathematical Society
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• v.40 no.1
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• pp.87-107
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• 2003

In this paper, we consider a discrete time queueing system fed by a superposition of an ON and OFF source with heavy tail ON periods and geometric OFF periods and a D-BMAP (Discrete Batch Markovian Arrival Process). We study the tail behavior of the queue length distribution and both infinite and finite buffer systems are considered. In the infinite buffer case, we show that the asymptotic tail behavior of the queue length of the system is equivalent to that of the same queueing system with the D-BMAP being replaced by a batch renewal process. In the finite buffer case (of buffer size K), we derive upper and lower bounds of the asymptotic behavior of the loss probability as $K\;\longrightarrow\;\infty$.

• Transactions of Materials Processing
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• v.25 no.3
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• pp.176-181
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• 2016

The exhaust tail pipe is the only visible part of the exhaust system on a vehicle. The conventional way to make the tail pipe is welding after stamping. There are various problems that occur during the stamping of stainless steel sheets such as scratching and local fracture. Problems during welding can also occur due to poor weldability. Tube hydroforming can be a solution, which eliminates these problems. The current study deals with the development of tube hydroforming for a vehicle tail pipe using finite element analysis for a free-feeding method. The current study focuses on the development of a proper load path for the tail pipe hydroforming and how bending influences the subsequent processing steps. The FE analysis results were compared with experimental results. This study shows the importance of bending and the necessity of considering bending when performing a tube hydroforming analysis.

• Journal of Aerospace System Engineering
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• v.6 no.2
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• pp.28-34
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• 2012

Structural integrity evaluation is important item in the aircraft certification. Recently, it is designed for limit load, material weakness about fatigue and corrosion, damage by bird strike in flight to evaluate structural integrity of aircraft. And static/fatigue analysis are performed to secure structural integrity, it was verified by static and fatigue tests. To evaluate the structural integrity of small aircraft tail, structural integrity was calculated by the finite element analysis. In the present study, finite element analysis are performed to pick out load cases in flight occurrence, and secure margin of safety to evaluate structural integrity of KC-100 tail unit. The proprieties of finite element analysis results are compared with the static structure test results. The estimation process of structural integrity for small aircraft tail may help the design.

• Proceeding of EDISON Challenge
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• 2016.11a
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• pp.90-95
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• 2016

본 연구에서는 교육 및 연구를 위한 CFD 해석 프로그램인 EDISON_CFD 프로그램을 이용하여 화물 트럭의 후면부 형상변화에 따른 공력특성을 분석해보았다. 먼저 추가적인 부착물을 장착하지 않은 기본적인 형상의 화물트럭의 공력특성을 확인 후, 후면부에 여러 형상의 Boat tail(보트 테일)과 전면부에 Cap-roof fairing(캡루프 페어링)이 부착된 형상을 해석하여 트럭이 받는 항력 감소를 통해 최적형상을 찾아가는 연구를 수행하였다. Cap-roof fairing이 부착된 형상에서 $15^{\circ}$의 특성길이가 0.3인 Boat tail에서 가장 좋은 항력 감소 효과를 얻을 수 있었다. Cap-roof fairing의 경우 6%의 항력 계수 감소를 보였고, Boat tail에서 20%의 항력 계수 감소효과를 관찰할 수 있었다. Boat tail의 각도와 길이를 변수로 하여 여러 해석을 진행한 결과 최적화된 형상을 선정할 수 있었다.