• Journal of Advanced Navigation Technology
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• v.24 no.2
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• pp.73-84
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• 2020

To overcome ground congestions due to growing number of cars, a lot of companies have proposed personal aerial vehicle (PAV). Among PAV, electric vertical take-off and landing (eVTOL) aircrafts capable of vertical take-off and landing with electric power are drawing attention, and their configurations vary from multicopters to tilt ducted fans. This study tries to analyze the characteristics of each eVTOL design configurations. Parasite drag was calculated using component build up method for Vahana, Aurora, Volocopter representing each eVTOL PAV type of tilt-wing, compound, and multicopter. Wetted area and induced drag was calculated using OpenVSP and XFLR5 that are aircraft design and aerodynamic analysis software. The batteries used in the eVTOL PAV was assumed as Tesla 2170 batteries and flight ranges were calculated. Also, energy consumption and maximum flight time for the given mission profile including take-off and landing, cruising segments were compared for each eVTOL.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.21 no.10
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• pp.144-149
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• 2020

Bubble reduction devices are intended to solve problems related to the quantitative supply of oil. Therefore, in this study, numerical analysis was conducted to verify the flow characteristics of bubble particles during the operation of a bubble reduction device. As a result of the basic analysis, the area where the rise and fall of bubbles were most active was found, and numerical calculations were performed focusing on the points. Before the numerical calculations, a non-dimensional derivation was performed to secure homogeneity among the variables. Based on the data obtained from non-dimension derivation, 25 variable conditions for each particle size and fluid velocity were set. Through separate calculations, the equation for bubble rise and fall was derived. By calculating the ratio of drag and buoyancy for each variable, if the drag force acting on the bubble was greater than buoyancy, the bubble falls, and bubbles are not reduced. If the buoyancy is larger than drag, the bubble rises, and the bubble is reduced. Through the analysis, the rise and fall of the bubble were confirmed, and the results were consistent with the separate numerical calculations.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.20 no.6
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• pp.532-539
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• 2008

Kwon et al.(2008) carried out a hydraulic experiment in order to evaluate Manning coefficient, which implicates flow resistance due to bottom friction as well as drag caused by the squared piers higher than water depth and arranged with equal intervals, under the flow condition with a constant drag coefficient, $Re>10^4$. And, based on the equation of equilibrium, they proposed a formula for the equivalent resistant coefficient including empirical drag interaction coefficient obtained by using the experimental results. In this study, the hydraulic experiment was simulated using FLOW-3D, a 3-dimensional computational fluid dynamic code. The computations were compared with the experiment results as well as the semi-theoretical formula, and the comparisons show a good agreement. From the agreement, it was confirmed that when flow resistance bodies were higher than water depth, Manning n value increases with 2/3 power of water depth as shown in the theoretical formula and that drag interaction coefficient was dominated by their intervals.

• Journal of the Korea Society for Simulation
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• v.28 no.1
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• pp.49-56
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• 2019

In this study aerodynamic characteristics of guided gliding type ammunition were investigated by using a computational analysis and wind tunnel test. Missile DATCOM, a semi-empirical method, and a FLUENT, a computational fluid dynamics analysis program, were used for computational analysis. For a guided gliding type ammunition, aerodynamic characteristics were investigated by calculating lift force, drag force, pitching moment and etc. Aerodynamic characteristics of guided gliding type ammunition are completely different from those of conventional ammunition. The results obtained from the computer analysis are similar to those obtained from the wind tunnel test. Although the pitch moment values obtained by the semi-empirical method were slightly different from the wind tunnel test results, the overall computer analysis results showed trends and values similar to the test results. In this study, aerodynamic characteristics of guided gliding type ammunition were identified and it found that semi-empirical method can be applied to analyze the aerodynamic characteristic in the initial design of guided gliding ammunition.

• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2017.04a
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• pp.54-54
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• 2017

본 연구는 무인 헬리콥터의 양력을 개선하기 위한 기초 단계로서 V1505A 및 V2008B 기본 두 익형의 400 mm 블레이드 섹션에 해당하는 모델에 대한 풍동실험을 실시하여 양력, 항력 및 동력특성을 분석하고 CFD 시뮬레이션의 결과와 비교하고 검증하였다. 시뮬레이션은 풍동 실험과 유사하게 설정하기 위하여 400 mm 블레이드 섹션의 양 끝을 벽으로 제한하여 3차원 와류현상을 억제하여 모델을 구성하였고, 시뮬레이션의 결과와 비교하여 모델을 검증하였다. 사용된 모델은 로터로부터 $Re=0.32{\times}10^6$ 영역까지는 aminar 모델을 사용하였으며, 그 이후 영역역(>$Re=0.32{\times}10^6$)은 양력 및 저항의 급격한 변화를 올바로 포착할 수 있다는 S-A 모델을 적용하여 확장하였다. 시뮬레이션의 격자는 유동 현상에 있어 박리로 야기된 와류 현상을 관찰하기 위하여 익형 주변에 접하는 부분에 격자를 집중시켰다. 시뮬레이션 방법은 유속은 36~141 m/s 까지 5 수준으로 하였으며, 받음각은 $0{\sim}16^{\circ}$로 7 수준으로 변화 시키면서 공력계수 및 동력을 분석하였다. 양력분석에 있어 익형 V1505A에 비해 익형 V2008B의 특성이 우수하였으나, 익형 V1505A는 실속 이후 양력이 급격히 떨어지지 않고 유지되는 특성을 보였다. 익형 V2008B는 낮은 받음각에서 높은 공력과 낮은 항력을 나타냈다. 동력 분석 결과로 익형 V1505A의 유도동력은 총 동력의 56~72%를 차지하고, 형상동력은 총 동력의 27~43%를 차지하였다. 익형 V2008B는 유도동력은 총 동력의 66~81%를 차지하고, 형상동력은 총 동력의 18~33%를 차지하였다. 익형 V2008B이 익형 V1505A보다 유도동력은 크며, 형상동력은 적게 나와 상대적으로 효율적이라 할 수 있다. 헬리콥터 동력원의 규모는 법률적인 총중량에 의하여 제한되므로 일반적인 농용 소형 무인 헬리콥터 엔진의 사양인 24.5 kW (32PS)를 적용한다면, 익형 V1505A은 받음각 $8{\sim}10^{\circ}$에서 그리고 익형 V2008B은 $7{\sim}9^{\circ}$정도에서 받음각이 제한되며 이때 총 양력은 1200~1300 N 정도로 예상된다.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.3 no.4
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• pp.244-254
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• 1991

The numerical analysis on tile behaviour of mooring system in the offshore guyed tower is presented. The governing equilibrium equations are derived by the principle of virtual work. The drag and inertia effects of fluid are included in a Morrison type equation. The finite element method is used in the computation. Geometric nonlinearities for the analysis of the mooring line are considered in which both modified Newton-Raphson method and Newmark-$\beta$ method are employed. Numerical experiments show the validity and the capability of the developed mathematical formulation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.3
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• pp.191-193
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• 2017

EFD-CFD Comparison Workshop was proposed based on the drag prediction workshop and high lift prediction workshop of AIAA. This workshop is organized to escalate the levels of wind tunnel test and computational fluid dynamics and to escalate the level of domestic aerodynamic technology through the collaboration of both areas. For three benchmark cases of which wind tunnel test results are available, comparison workshops have been held since 2015.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05a
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• pp.596-602
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• 1998

한국의 차세대 원자로 (Korean Next Generation Reactor; KNGR)에 처음 적용되는 격납건물내에 설치된 재장전수조 (In-Containment Refueling Water Storage Tank; IRWST)는 기존 재장전수조의 기능외에 주입모드에서 재순환 모드를 전환생략, 일차계통으로 방출된 고온, 고압 냉각수의 응축 및 냉각 격납용기 방사능 오염방지, 원자로 동공층수 등 여러 가지 추가 기능을 가진 한층 진보된 설계개념이다. 발전소 천이사고 시 발생하는 Pipe Clearing, 응축진동 현상(Condensation Oscillations), Chugging 등의 열수력 현상들이 방출증기의 유동 및 가속도와 관련해 항력과 응력, 압력진동 등을 일으켜 IRWST 구조물에 영향을 미칠 수 있기 때문에 IRWST를 처음으로 시도하는 우리 나라로서는 이와 관련된 제반현상에 대한 심도 깊은 연구가 요구된다. 따라서 본 연구에서는 원자력 발전소 과도로 인한 가압기 안전밸브(Pressurizer Safety Valve) 또는 안전감압밸브(Safety Depressurization Valve) 작동시 IRWST로 방출되는 유체로 야기되는 하중 예측 모델을 기존의 BWR의 응축수조(suppression Pool)에서 일어나는 각종 현상을 토대로 이론적으로 체계적으로 유도하여 이를 비교, 분석하였다.

• Proceeding of EDISON Challenge
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• 2013.04a
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• pp.437-441
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• 2013

항공기의 날개에 걸리게 되는 하중은 설계단계에서 고정되기 때문에 이륙과 착륙 같은 특수한 상황에서는 Flap이나 슬렛 등의 고양력 장치를 이용하여 날개 단면 형상을 변화시킴으로서 양력계수의 변화를 유도하고 그에 따라 각 임무별 최적의 공력 성능을 제공할 수 있게 된다. 따라서 본 논문은 에어포일의 보다 효율적인 양력을 위해 slotted flap사이에 양력 향상 Tab을 설치하여 EDISON-CFD을 이용하여 분석하였다. 그리고 그 효과와 익형에 얻어지는 양력계수를 비교하였다. 에어포일의 Slotted Flap에 양력 향상 Tab의 유무에 따른 유동 장을 분석하여 양력을 수치 해석 적으로 비교해 보았다. 결과에서 얻어진 상수를 비교하였고 양력 향상 Tab의 효과를 분석해 보았다.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.28 no.6B
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• pp.635-642
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• 2008

The influence of unsubmerged resistance bodies in a channel turbulence flow on energy loss was investigated by hydraulic experiments. Square-shaped multi-piers were used for unsubmerged structure or rigid vegetation in an open channel. In experimental channel flows multi-piers were arranged in double or single row along the channel direction, and mean-concept uniform elevations were attained and measured with a set of discharges and channel slopes. Applying the experimental results to the Manning equation, the equivalent resistance coefficient n, which implicates flow resistance and energy loss due to bottom friction as well as drag, was evaluated with varying the interval of piers and the uniform water depth. And the experimentally evaluated n values were compared with the semi-theoretical formula of the equivalent resistance coefficient derived from momentum analysis including a drag interaction coefficient. From the comparisons it was found that the interaction effect of piers on flow resistance was significant for the overall energy losses in a channel flow. The n values decrease when the interval of piers in flow-direction is less than about 2.2 times of the pier width. And it was also found that the n values increase with the 2/3 power of water depth in the theoretical formula, since the drag interaction coefficient was found to be mostly dependent on the interval of piers.