• Journal of Ocean Engineering and Technology
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• v.27 no.3
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• pp.73-78
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• 2013

CFD (computational fluid dynamics) analyses that considered the dynamic interaction effects between the flow and a turbine were performed to evaluate the power output characteristics of two representative vertical-axis tidal-current turbines: an H-type Darrieus turbine and Gorlov helical turbine (GHT). For this purpose, a commercial CFD code, Star-CCM+, was utilized, and the power output characteristic were investigated in relation to the scale ratio using the relation between the Reynolds number and the lift-to-drag ratio. It was found that the power coefficients were significantly reduced when the scaled model turbine was used, especially when the Reynolds number was lower than $10^5$. The power output characteristics of GHT in relation to the twisting angle were also investigated using a three-dimensional CFD analysis, and it was found that the power coefficient was maximized for the case of a Darrieus turbine, i.e., a twisting angle of $0^{\circ}$, and the torque pulsation ratio was minimized when the blade covered $360^{\circ}$ for the case of a turbine with a twisting angle of $120^{\circ}$.

• Proceeding of EDISON Challenge
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• 2014.03a
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• pp.574-578
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• 2014

본 연구에서는 인접 구조물의 상호 간섭에 의한 풍압 변화에 대한 분석을 수행하였다. 두 개의 구조물 사이의 거리 및 위치를 변경하여 비교 해석하는 것으로써 사각형 구조물 구현을 위해 EDISON_CFD를 이용하여 수치해석을 하였고, 유한 체적 법(Finite Volume Method, FVM) 기반의 범용 비압축성 유동 해석을 위해 2D_Incomp-P_2.1 해석자를 사용하였다. 이 연구를 통하여 인접한 구조물의 영향을 분석하여 상호 간 거리와 위치를 결정할 수 있는 근거자료를 확보하였다.

• Proceedings of the Korean Vacuum Society Conference
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• 2016.02a
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• pp.182.2-182.2
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• 2016

Hollow cathode discharge(중공 음극)는 음극 표면에서 발생되는 2차 전자를 이용하여 높은 밀도의 플라즈마를 만들 수 있는 장점이 있다. 전원으로 microwave, RF, DC, pulsed dc등을 사용할 수 있으며 박막의 증착, 식각 등에 응용 가능하다. 물리적 현상으로는 중공 음극 재료 표면 물질의 가열 및 이온 스퍼터링, 2차 전자의 가열, 자기장 인가 구조의 경우 전자 거동이 있다. PIC(particle-in-cell)방식의 모델링과 fluid model을 이용한 방법이 있는데 본 연구에서는 상용 fluid model software인 ESI사의 CFD-ACE+를 사용하여 모델링 하였다. 구동 주파수는 13.56 MHz의 상용 고주파 전원과 보다 낮은 1 MHz, 100 kHz의 수치 모델을 이용하여 HF, MF, LF 영역에서의 동작 특성을 해석하였다. 1차적으로는 가스 유동의 특성을 2D, 3D로 조사하였고 플라즈마 거동은 2차원을 주로 진행하였으며 계산 시간이 오래 거리는 3차원 모델을 하나 만들어 그 특성을 조사하였다.

• The KSFM Journal of Fluid Machinery
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• v.16 no.2
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• pp.10-14
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• 2013

The present study conducts CFD analyses on the internal flow fields of roots type vacuum pumps of semiconductor fabrication facility, and the computed CFD results for internal pressure and temperature distributions are applied to structural analyses of the pumps. The coupled analysis results between flow and structure show that the deformation of pump structure is mainly resulted from the thermal expansion of gas in pump, and the deformed impeller and housing produce their severe contact and impact phenomena causing mechanical damage and fracture.

• Proceedings of the KSME Conference
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• 2004.04a
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• pp.1171-1176
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• 2004

To develop and improve a switchgear, the prediction of the pressure rising within the switchgear is very important. This study investigates the pressure rising characteristics of switchgear in order to evaluate the result of arc fault test. The pressure rising time at the four points of measurement calculated by CFD is well accord with the experimental results. The maximum pressure within the switchgear estimated by CFD is about 1.0bar, the pressure from experiment is 0.7 bar. The results of this study are able to be used to improve the performance of existing switchgear and to develop a new type switchgear.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.73-80
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• 2013

In this study, a numerical analysis based on CFD methods has been conducted to predict the aerodynamic coefficients and aerodynamic loads of KSLV-II configuration designed at the system design phase. By the effects of exclusion of engine cowls of prior configuration, axial force and normal force decreased and center of pressure was much moved to the nose direction. Also, aerodynamic loads at flight and on the launch pad were predicted for structural load analysis. The computed results will be used for mission analysis and structural analysis at the next design phase.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.6
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• pp.72-83
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• 2018

In this study, a series of CFD analyses were carried out for a hydrogen rocket combustor with a single shear coaxial injector. A hybrid RANS/LES approach was used for the turbulent combustion analysis with a two-dimensional axisymmetric configuration. Three reaction mechanisms, three spatial discretization methods, and three levels of grid resolution were compared to determine an appropriate CFD approach. The performance of the CFD prediction were investigated by comparing the wall heat flux with experimental data. Investigation of the flow field results provides an insight into the characteristics of the turbulent reacting flow of a rocket combustor with a shear coaxial injector.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.30 no.11 s.254
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• pp.1057-1065
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• 2006

In order to figure out the physical meaning of 3-D angular flow index for in-cylinder bulk motion, CFD analysis for the swirl and tumble steady flow test rig were made using commercial package STAR-CD. Computer simulations and rig tests on some kinds of induced flow conditions were carried out. Finally, based on the comparison between the simulated results and measured results, the physical meaning of 3-D angular flow index $|\longrightarrow_{N_B}|$, $\beta$ composed of swirl and tumble coefficients measured by steady flow test rig was described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.215-218
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• 2011

An air data acquisition algorithm has been developed for the supersonic flow at the preliminary design stage with pressure data acquisition device composed of major three total pressure sensors and two static pressure sensors. Through this algorithm, Mach number, angle of attack and sideslip angle can be very easily derived with simple interpolation algorithm and predefined data tables. In this preliminary design stage, to verify the developed algorithm, the data tables are constructed with data driven by Taylor Maccoll equation. Furthermore, these data are compared and modified with computational results based on CFD analysis. The present algorithm would be useful to get supersonic air data for the various aerial vehicles and their flight tests.

• Proceedings of the KSR Conference
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• 2011.10a
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• pp.1594-1600
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• 2011

Recently developed FDS5 CFD code has employed a near-wall flow treatment method which is Werner-Wengle wall law provided by NIST(National Institute of Standards and Technology). In this study, the wall law has been verified against DNS(Direct Numerical Simulation) data in the parallel plate. The $y^+$ was kept above 11 to fulfill the near-wall flow requirement in the grid generation. The total grid was $32{\times}32{\times}32$. The boundary condition for inlet and outlet was periodic condition and for both side, symmetric condition was used. The fully developed turbulent flow was generated and Re = 10,700. The simulated results were compared with DNS data. RANS results were also used for verification.