• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.3
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• pp.212-216
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• 2017

Aerodynamic analysis for the airfoil, KARI-11-180 having 18% thickness ratio, was performed with CFD techniques. The boundary layer grid was generated by projecting the wall grid normally and fine grid was placed behind the trailing edge to capture the wake accurately. The distance to the far boundary is 100 chords and the flow condition is same as the wind tunnel test condition. Transition SST and DES turbulence models were utilized for accurate prediction of the transiton point. The predicted lift is higher but the drag is predicted lower than the wind tunnel test. 3-dimensional results with airfoil models of which aspect ratio were 2 and 5 were compared with 2-dimensional results.

• Proceedings of the KSME Conference
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• 2001.11b
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• pp.563-569
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• 2001

The head-capacity curves for pumps developed by the pump manufacturer are based on tests of a single pump operating in a semi-infinite pool with no nearby walls or floors and no stray currents, Hence, flow into the pump suction is symmetrical with no vortices or swirling. Pump station designers rely on these curves to define the operating conditions for the pump selected. But various constraints such as size, cost, and limitations on storage time require walls, floors, and pump intakes to be close proximity to each other. From this background, the authors are carrying out a systematic study on the flow characteristics of intakes within a sump found in pump stations. Model pump intake basin is designed and PIV is adopted as a measuring tool to capture the instantaneous flow patterns. Special attention is paid to investigate the flow patterns near the free surface, side-wall and back-wall due to different clearances from back-wall to vertical in take pipe. Moreover, the locations and vorticities of the various types of vortices that were found in the examinations are discussed.

• Journal of the Society of Naval Architects of Korea
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• v.29 no.4
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• pp.66-74
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• 1992

A panel method in the spirit of Hess & Smith(1962), and also of Dawson(1977) was developed to compute the wave resistance of a submerged, or a surface piercing, body moving in the water of finite depth. As a boundary condition on the free surface what is called the Poisson equation is used, while Yasukawa(1989) chose the Dawson equation for which the double-body flow is regarded as the basic one. In order to satisfy the boundary condition on the bottom surface automatically, the sum of a Rankine source and its image with respect to the bottom surface is chosen as the Green function, and hence the singularity is distributed only on the body and on the free surface thereby decreasing the required number of panels dramatically, compared to that of Yasukawa, without the consequential loss of accuracy. Calculations were done for a submerged sphere and for the Wigley hull, and the results are compared with other existing analytical and numerical data.

• The Sea:JOURNAL OF THE KOREAN SOCIETY OF OCEANOGRAPHY
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• v.5 no.2
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• pp.77-85
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• 2000

Simulation of local external forcing and its response in the rotation table experiment has been investigated. Spatially-uniform external forcings have been applied in many experimental studies, however, based on the fact that the north-south distribution of the wind-stress curl and the existence of local maximum of the sea surface heat loss in the northern part of the East Sea, new method of combined effects of local forcings has been employed in separate experiments. Carefully designed local source or sink at the bottom of the cylindrical container can produce horizontal pressure gradient within the Ekman layer, and consequently the interior also attains the same pressure gradient that produces geostrophic interior circulation. In order to keep free surface during the local-surface cooling, a side-wall cooling method is suggested. For the various type of local forcing including the effects local cooling and the periodic change of local wind-stress curl, western-boundary flow in terms of its strength, position of separation from the boundary have been observed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.12
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• pp.831-840
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• 2019

Flush Air Data Sensing system (FADS) estimates air data states using pressure data measured at the surface of flight vehicles. The FADS system does not require intrusive probes, so it is suitable for high performance aircrafts, stealth vehicles, and hypersonic flight vehicles. In this study, calibration procedures and solution algorithms of the FADS for a sphere-cone shape vehicle are presented for the prediction of air data from subsonic to supersonic flights. Five flush pressure ports are arranged on the surface of nose section in order to measure surface pressure data. The algorithm selects the concept of separation for the prediction of flow angles and the prediction of pressure related variables, and it uses the pressure model which combines the potential flow solution for a subsonic flow with the modified Newtonian flow theory for a hypersonic flow. The CFD code which solves Euler equations is developed and used for the construction of calibration pressure data in the Mach number range of 0.5~3.0. Tests are conducted with various flight conditions for flight Mach numbers in the range of 0.6~3.0 and flow angles in the range of -10°~+10°. Air data such as angle of attack, angle of sideslip, Mach number, and freestream static pressure are predicted and their accuracies are analyzed by comparing predicted data with reference data.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.7
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• pp.616-621
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• 2014

Consumption of the fuel on the satellite operating in low earth orbit, is increased due to the air resistance and the amount of increase makes the satellite lifetime decrease or the satellite mass risen. Therefore the prediction of drag force of the satellite is important. In the paper, drag force and drag coefficient analysis of the parabolic antenna satellite in low earth orbit using direct simulation monte carlo method (DSMC) is conducted according to the mission altitude and angle of attack. To verify the DSMC simulated rarefied air movement, Starshine satellite drag coefficient according to the altitude and gas-surface interaction are compared with the flight data. Finally, from the analysis results, it leads to appropriate satellite drag coefficient for orbit lifetime calculation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.8
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• pp.747-757
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• 2010

The ice accreted on the airfoil is one of the critical drivers that causes the degradation of aerodynamic performance as well as aircraft accidents. Hence, an efficient numerical code to predict the accreted ice shape is crucial for the successful design of de-icing and anti-icing devices. To this end, a numerical code has been developed for the prediction of glaze ice accretion shape on 2D airfoil. Constant Source-Doublet method is used for the purpose of computational efficiency and heat transfer in the icing process is accounted for by Messinger model. The computational results are thoroughly compared against available experiments and other computation codes such as LEWICE and TRAJICE. The direction and thickness of ice horn are shown to yield similar results compared to the experiments and other codes. In addition, the effects of various parameters - temperature, free-stream velocity, liquid water contents, and droplet diameter - on the ice shape are systematically analyzed through parametric studies.

• Transactions of the Korean Society of Mechanical Engineers
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• v.14 no.3
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• pp.702-715
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• 1990

This paper describes behaviors of two-phase open channel flow inside the flash chamber of a horizontal Multi-Stage-Flash evaporator numerically along with the experimental observations. Bubble trajectories and the velocity and temperature distributions of the liquid phase were predicted by using the particle-source-in-cell(PSI-Cell) method with the appropriate bubble motion/growth equations. Size and number of bubble nuclei embedded in the incoming liquid(brine) were taken into account as important parameters in addition to the conventional ones such as the velocity, degree of inlet superheat, inlet opening height, and the liquid level. Bubble motions, which are unsteady, appeared to be mostly determined by the buoyancy and the drag forces. The calculations, though a number of simplifying assumptions were made, reasonably simulated the hydrodynamic behaviors of the two-phase horizontal stream observed in the experiments. The simulated temperature distributions also agreed fairly well with the other's measurements. Non-equilibrium allownaces, evaluated from the simulated temperature distributions, were within the range of those obtained from the existing correlations, and reduced with the increases of the number and size of incoming bubble nuclei due to vigorous flashing.

• Bulletin of the Society of Naval Architects of Korea
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• v.25 no.4
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• pp.13-27
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• 1988

Two version of the TUMMAC(Tokyo University Modified Marker-And-Cell) method, i.e., $TUMMAC-IV_{vm1}$ and TUMMAC-VI are applied to two water-wave problems. The ship wave of a Series 60 model($C_B=0.6$) and of the fore-body of a HSVA tanker model are simulated by the $TUMMAC-IV_{vm1}$ method are the results are compared with the experimental results. From the comparison with the experimental data it is ascertained that the $TUMMAC-IV_{vm1}$ method is useful for the analysis of the realized by the TUMMAC-VI method is useful for the analysis of the characteristics of nonlinear ship waves. Three-dimensional wave breaking is realized by the TUMMAC-VI method in the simulation of a flow about a vertical rectangular cylinder. From the results of this simulation, it is shown that the TUMMAC-VI method is very available for the simulation of 3-dimensional wave breaking phenomena.

• 한국HCI학회:학술대회논문집
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• 2006.02a
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• pp.1031-1036
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• 2006

햅틱 분야는 디스플레이 되는 콘텐츠를 만질 수 있게 촉감을 제공함으로써 의학, 교육, 군사, 방송 분야 등에서 널리 연구되고 있다. 이미 의학 분야에서는 Reachin 사(社)의 복강경 수술 훈련 소프트웨어와 같이 실제 수술 할 때와 같은 힘을 느끼면서 수술 과정을 훈련할 수 있는 제품이 상용화 되어 있다. 그러나 햅틱 분야가 사용자에게 시청각 정보와 더불어 추가적인 촉감을 제공함으로써 보다 실감 있고 자연스러운 상호작용을 제공하는 장점을 가진 것에 비해 아직은 일반 사용자들에게 생소한 분야다. 그 이유 중 하나로 촉감 상호작용이 가능한 콘텐츠의 부재를 들 수 있다. 일반적으로 촉감 콘텐츠는 컴퓨터 그래픽스 모델로 이루어져 있어 일반 그래픽 모델러를 사용하여 콘텐츠를 생성하나 촉감과 관련된 정보는 콘텐츠를 생성하고 나서 파일에 수작업으로 넣어주거나 각각의 어플리케이션마다 직접 프로그램을 해주어야 한다. 이는 그래픽 모델링과 촉감 모델링이 동시에 진행되지 않기 때문에 발생하는 문제로 촉감 콘텐츠를 만드는데 시간이 많이 소요되고 촉감 정보를 추가하는 작업이 직관적이지 못하다. 그래픽 모델링의 경우 눈으로 보면서 콘텐츠를 손으로 조작할 수 있으나 촉감 모델링의 경우 손으로 촉감을 느끼면서 동시에 조작도 해야 하기 때문에 이에 따른 인터페이스가 필요하다. 본 논문에서는 촉감 상호작용이 가능한 촉감 콘텐츠를 직관적으로 생성하고 조작할 수 있게 하는 촉감 모델러를 기술한다. 촉감 모델러에서 사용자는 3 자유도 촉감 장치를 사용하여 3 차원의 콘텐츠를 실시간으로 만져보면서 생성, 조작할 수 있고 촉감 사용자 인터페이스를 통해서 콘텐츠의 표면 촉감 특성을 직관적으로 편집할 수 있다. 촉감 사용자 인터페이스는 마우스로 조작하는 기존의 2차원 그래픽 사용자 인터페이스와는 다르게 3 차원으로 구성되어 있고 촉감 장치로 조작할 수 있는 버튼, 라디오 버튼, 슬라이더, 조이스틱의 구성요소로 이루어져 있다. 사용자는 각각의 구성요소를 조작하여 콘텐츠의 표면 촉감 특성 값을 바꾸고 촉감 사용자 인터페이스의 한 부분을 만져 그 촉감을 실시간으로 느껴봄으로써 직관적으로 특성 값을 정할 수 있다. 또한, XML 기반의 파일 포맷을 제공함으로써 생성된 콘텐츠를 저장할 수 있고 저장된 콘텐츠를 불러오거나 다른 콘텐츠에 추가할 수 있다.