• Proceedings of the Korea Water Resources Association Conference
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• 2011.05a
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• pp.238-238
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• 2011

복단면 하도는 홍수소통을 위한 상부 하도와 생태계 서식처 강화와 유사이송능력 개선, 경제적인 유지유량의 확보 등을 도모하는 자연적인 저수로 하도로 구성된다. 그러므로 갈수기와 홍수기의 유량차가 큰 하천에서, 복단면 하도는 하천 공학, 환경 생태 관점에서 다양한 이점을 제공한다. 그러나 복단면 하도에서의 흐름저항, 조도계수, 통수능, 수위-유량관계, 횡방향 유속분포, 그리고 하상전단응력 분포는 단단면 하도와 상이하며, 중요한 차이점은 주수로부와 홍수터부 사이의 유속차로 인하여 발생하는 활발한 운동량 교환에 의해 추가적인 전단층이 생성되는 점이다. 주수로와 홍수터 사이에서 발생된 경계전단력(Apparent Shear Force, ASF)은 하천의 전반적인 통수능을 감소시켜 홍수의 하도내 저류효과를 증가시킬 수도 있다. 또한 주수로 및 홍수터가 분담할 수 있는 유량은 경계전단력에 민감하기 때문에, 홍수터에 수목 식재, 구조물 설치 등을 계획할 경우 정량적인 항력저항의 산정을 위하여 매우 중요하다. 현재까지 복단면에서 발생하는 경계전단응력을 추정하는 다양한 방법들이 개발되었으며, 각각의 방법으로 부터 경계전단력을 정량적으로 예측할 수 있다. 그러나 대부분의 방법이 실험에 근거한 경험적 방법이므로 각 식의 개발에 사용된 자료에만 적합할 수 있는 한계가 있으며, 균일한 수로의 기하학적 변수(전단면과 주수로의 하폭비, 홍수터와 주수로의 수심비, 홍수터와 주수로의 조도비, 주수로의 하폭대 수심비 등)에 의한 식으로 구성되어 수치모형에서 직접 활용하기에는 한계가 있다. 따라서 본 연구에서는 복단면 경계전단력 산정을 위하여 개발된 다양한 연구결과들을 비교 검토하고, 기존문헌 또는 웹상에서 가용한 수리실험 자료들을 이용하여 각 방법에서 계산된 유량과 실측 유량을 비교함으로써 각 방법이 지닌 한계를 분석하였다. 본 연구에서 검토된 5가지 방법은 Knight and Demetriou (1983)(이하 KD), Wormleaton and Merret (1990)(이하 WM), Cristodoulou (1992), Bousmar and Zech(1999) (이하 BZ) 그리고 Moreta and Martin-Vide (2010)(이하 MM)이다. BZ 방법을 제외하고 나머지 방법들은 전체 유량의 비교에서 5% 이내의 오차를 나타내었다. 그러나 나머지 4가지 방법 중 주수로부 유속의 비교에 있어서는 소규모 수로 실험자료만 이용한 KD 방법이 5% 이상의 오차를 나타내어 정확도가 떨어지는 것으로 나타났다. 따라서 비교적 단순한 형태의 Cristodoulou (1992) 방법이 적용하고자 하는 수로의 규모와 무관하게 복단면 유량예측에 적합할 것으로 판단된다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.2
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• pp.97-108
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• 2015

In the design of sailing yachts, para-glider, or high-sky wind power, etc., the analysis of side-wind aerodynamic forces exerted on a cambered 3-D model is very important to predict the performance of various machinery systems. To understand the essential flow physics around the three-dimensional shape, simplified rigid-body models are proposed in this study. Four parameters such as free stream velocity, angle of attack, aspect ratio, and camber are considered as the independent variables. Lift and drag coefficients are computed with CFD technique using ANSYS-CFX, and the results with the visualization of post-processed flow fields are analyzed in the viewpoint of fluid dynamics.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.8
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• pp.711-717
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• 2012

During the conceptual design phase of a light sport aircraft, the wind tunnel tests were conducted to investigate the static stability of newly-designed configuration. The 1/5 scale-down wind tunnel model consisted of fuselage, main wing, vertical tail and horizontal tail. The main wing and tails were able to be attached or detached from the fuselage. The aerodynamic forces and moments acting on the 6 different configurations compounding each component were measured by using the internal balance system and their static stability derivatives were derived. With these experimental data, the baseline lift and drag characteristics as well as the effects of each component to the longitudinal, directional and lateral static stability were quantitatively analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.4
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• pp.281-289
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• 2016

Accurate prediction of the trajectory and time of a time-varying mass parachute system remains essential in the mission requiring a precision airdrop to the ground. In this study, we investigate the altitude-varying behavior of a cross-type parachute system designed to deliver a time-varying mass object like flare. The dynamics of the descending parachute system was analyzed based on the Runge-Kutta method of the ordinary differential system. The drag coefficients of the cross-type parachute and flare were calculated by a CFD code based on the incompressible Navier-Stokes equation. Finally, by using a simplified gust wind model in troposphere, the combined effects of gust wind and time-varying mass were examined in detail.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.984-990
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• 2017

Mesh screen modeling and liquid propellant discharge simulation of surface tension tank were performed using commercial CFD software Flow-3d. $350{\times}2600$, $400{\times}3000$ and $510{\times}3600$ DTW mesh screen were modeled using macroscopic porous media model. Porosity, capillary pressure, and drag coefficient were assigned for each mesh screen model, and bubble point simulations were performed. The mesh screen model was validated with the experimental data. Based on the screen modeling, liquid propellant discharge simulation from PMD tank was performed. NTO was assigned as the liquid propellant, and void was set to flow into the tank inlet to achieve an initial volume flow rate of liquid propellant in $3{\times}10^{-3}g$ acceleration condition. The intial flow pressure drop through the mesh screen was approximately 270 Pa, and the pressure drop increased with time. Liquid propellant discharge was sustained until the flow pressure drop reached approximately 630 Pa, which was near the estimated bubble point value of the screen model.

• Journal of the Korean Society for Marine Environment & Energy
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• v.6 no.2
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• pp.63-71
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• 2003

The main functions of containment boom for marine floating debris are to prevent spreading of the marine floating debris and to effectively collect the trash skimmer. The design characteristics of containment boom for marine floating debris in wave, current and wind are investigated. The response of a containment boom on the current is a function of a number of parameters, such as geometric characteristics, buoyance/weight ratio and towing velocity. To understand the relationship between these design parameters more clearly, a series of tests with three models with the variation of current speed and gap ratio was conducted. The model tests results are developed to new numerical equation that is tension prediction method of containment boom for marine floating debris. Also its is compared with open sea experimental results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.532-540
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• 2008

Recently there are growing interests in calculating aerodynamic characteristics of aircraft configurations with structural deformation using the FSI(Fluid-Structure Interaction) system in which CFD(Computational Fluid Dynamics) and CSD(Computational Structure Dynamics) modules are coupled. In this paper the FSI system comprised of CAD, CFD, CSD, VSI(Volume Spline Interpolation) and grid deformation modules was constructed in order to investigate aerodynamic characteristics of the deformed shape. In the process VSI and grid generation modules are developed to combine CSD and CFD routines and to regenerate the aerodynamic grids for the deformed shape, respectively. For the CFD and CSD analysis, commercial programs FLUENT and NASTRAN were used. As a test model, DLR-F4 wing configuration was chosen and its aerodynamic characteristics were calculated by applying the static FSI system. It was shown that lift and drag coefficients of the wing at mach number 0.75 are reduced to 20.26% and 18.5%, respectively, owing to the structural deformation.

• Proceedings of the Korea Water Resources Association Conference
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• 2015.05a
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• pp.395-395
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• 2015

하천 내 식생은 수리학, 지형학 및 생태학적으로 매우 중요하다. 식생은 하천 수생물들의 서식처를 제공할 뿐만 아니라 필터와 같은 역할을 함으로써 부유사에 의한 하천오염물의 퇴적을 유발하여 하천의 수질을 개선시킨다. 더욱이, 하천 내 흐름 및 난류구조를 변경시킴으로써 식생주변의 유사 퇴적량 및 분포에 크게 영향을 미치고, 결국 하천의 지형을 변화시킨다. 개수로의 식생에 대한 영향은 주로 실험 및 수치모델을 이용하여 연구되었고 전단면이 식재된 조건에서 식생의 항력계수, 식생역내의 부유사 및 확산에 관한 연구가 진행되어왔다. 이러한 연구를 통해 식생역 내의 전단력이 감소하여 부유사퇴적이 증가하고 식생역과 비식생역 사이의 운동량 교환에 의해 부유사 퇴적이 증가함을 보였다. 그러나 개수로에서 존재하는 유한한 크기의 식생에 의한 흐름 및 유사분포에 관한 연구는 아직 미흡하다. 이에 본 연구에서는 침수하지 않은 원형 식생 주변에서 발생하는 흐름특성을 수치모의 하였다. 침수하지 않은 원형식생 하류에서 발생하는 흐름을 계산하기 위해 2차원 수치모형을 적용하였다. 식생에 의한 저항을 고려하기 위해 운동량 방정식에 식생항을 추가하였고 $k-{\varepsilon}$ 난류모형을 적용하였다. 수치모의 조건은 Zong and Nepf (2012)의 수리실험을 참고하여 수로의 길이는 12 m, 폭은 1.2 m로 설정하였다. 0.13 m 수심을 갖는 개수로에 0.22 m 지름을 갖는 원형식생을 상류경계로부터 1.0 m 떨어진 곳에 설정하였다. 식생의 밀도($6{\sim}77m^{-1}$)를 변화시키면서 원형식생 하류의 흐름거동을 분석하였다. 식생밀도가 높은 경우에는 원형식생 양 측면에서 유발된 전단층들의 상호작용에 의해 하류에서 와류가 발생하였다. 와류가 발생하는 위치에서 난류강도가 가장 크게 나타났다. 그러나 식생밀도가 일정 값보다 낮아지면 와류가 발생하지 않는 것으로 나타났다.

• Journal of Advanced Navigation Technology
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• v.25 no.1
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• pp.29-39
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• 2021

As a means of solving traffic congestion in the downtown of large city, the interest in urban air mobility (UAM) using electric vertical take-off landing personal aerial vehicle (eVTOL PAV) is increasing. eVTOL configurations that will be used for UAM are classified by lift-and-cruise, tilt rotors, tilt-wings, tilted-ducted fans, multicopters, depending on propulsion types. This study tries to perform preliminary conceptual design for a given mission profile using reverse engineering techniques by taking the multicopter type Airbus's CityAirbus as a basic model. Wetted area, lift to drag ratio, drag coefficients were calculated using the OpenVSP which is an aerodynamic analysis software. The power required for each mission section of CityAirbus were calculated, and the corresponding battery and motor were selected. Also, total weight was predicted by estimating component weights of eVTOL.

• Journal of Bio-Environment Control
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• v.17 no.2
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• pp.83-89
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• 2008

A wind tunnel test was conducted at Protected Horticulture Experiment Station of National Horticultural Research Institute in Busan to find the aerodynamic resistance and quadratic resistance coefficient of chrysanthemum in greenhouse. The internal plants of the CFD model has been designed as a porous media because of the complexity of its physical shapes. Then the aerodynamic resistance value should be input for analyzing CFD model that crop is considered while the value varies by crops. In this study, the aerodynamic resistance value of chrysanthemum canopy was preliminarily found through wind tunnel test. The static pressure at windward increased as wind velocity and planting density increased. The static pressure at leeward decreased as wind velocity increased but was not significantly affected by planting density. The difference of static pressure between windward and leeward increased as wind velocity and planting density increased. The aerodynamic resistance value of chrysanthemum canopy was found to be 0.22 which will be used later as the input data of Fluent CFD model. When the planting distances were $9{\times}9\;cm$, $11{\times}11\;cm$, and $13{\times}13\;cm$, the quadratic resistance coefficients of porous media were found to be 2.22, 1.81, and 1.07, respectively. These values will be used later as the input data of CFX CFD model.