• 한국해양공학회지
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• 제28권6호
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• pp.508-516
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• 2014

A numerical method to investigate the non-linear motion characteristics of a TLP is established. A time domain simulation that includes the memory effect using the convolution integral is used to consider the transient effect of TLP motion. The hydrodynamic coefficients and wave force are calculated using a potential flow model based on the HOBEM(higher order boundary element method). The viscous drag force acting on the platform and tendons is also considered by using Morison’s drag. The results of the present numerical method are compared with experimental data. The focus is the nonlinear effect due to the viscous drag force on the TLP motion. The ringing, springing, and drift motion are due to the drag force based on Morison's formula.

• 대한기계학회논문집B
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• 제38권12호
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• pp.1009-1015
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• 2014

본 연구는 NACA0012 천음속 에어포일 유동에 있어서 비평형 응축이 Force 계수(압력, 양력 및 항력계수)에 미치는 영향을 TVD 수치해석을 통하여 연구하였다. 정체점 온도 298 K, 받음각 ${\alpha}=3^{\circ}$인 경우, 주류 마하수 0.78~0.81에서는 정체점 상대습도의 증가함에 따라 양력은 단순 감소한다. 반면 Lift force break 마하수 영역의 주류 마하수에서는 정체점 상대습도의 증가에 따라 양력은 오히려 증가한다. 받음 각 ${\alpha}=3^{\circ}$, 정체점 상대습도가 0%인 경우, 주류 마하수의 증가에 따라 항력은 급격하게 증가하지만, 응축의 영향이 큰 60%인 경우에는 주류 마하수의 증가에 조금 증가할 뿐이다. 동일한 주류 마하수인 경우 비평형 응축에 따른 전 항력의 감소는 받음각과 정체점 상대습도가 증가할수록 크게 된다. 응축이 없는 ${\Phi}_0=0%$인 경우는 주류 마하수가 크고 받음각이 클수록 Wave drag은 크게 되나 응축의 영향이 비교적 큰 ${\Phi}_0=50%$ 이상인 경우는 오히려 Wave drag이 작아지는 것으로 나타났다. 한편, 정체점 상대습도가 낮고, 주류 마하수가 클수록 충격파 직전의 최대 마하수는 커지는 것으로 나타났다.

• 한국해양공학회지
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• 제16권2호
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• pp.10-20
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• 2002

본 논문에서는 바다의 자유표면에서 생성되는 항력에 대한 물리적 특성에 대한 연구가 기술되었다. 2차원 파장(Wave Field) 매개변수해석기법(Parametric Analyzing Technique)을 근거로 한 파경계층(Wave Boundary Layer : WBL)의 1차원 모델로서 항력계산과 파경계층의 특성을 추정하였으며 이론의 간략화(Simplifying)에 대한 연구에 주력하였다.

• 한국분무공학회지
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• 제9권3호
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• pp.42-49
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• 2004

The present article investigates the influence of droplet drag models on predictions of diesel spray behaviors under ultra-high injection pressure conditions. To consider drop deformation and shock disturbance, this study introduces a new hybrid model in predicting drag coefficient from the literature findings. Numerical simulations are first conducted on transient behaviors of single droplet to compare the hybrid model with earlier conventional model. Moreover, using two different models, extensive numerical calculations are made for diesel sprays under ultra-high pressure sprays. It is found that the droplet drag models play an important role in determining the transient behaviors of sprays such as spray tip velocity and penetration lengths. Numerical results indicate that this new hybrid model yields the much better conformity with measurements especially under the ultra-high injection pressure conditions.

• 한국항만학회지
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• 제10권1호
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• pp.15-23
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• 1996

In this paper, the numerical model to analyze the wave absorbing performance of upright perforated plates is developed under the linear potential theory. If the drag force is dominent to the inertia force in passing perforated plate, the characteristics of perforated plates are determined by a nondimensionlized real-value of G or a length scaled real-value of a. The parameters (G,a), which depend on the drag coefficient, porosity and local shape of plates, can be readily obtained by simple experiments. We investigated the reflection coefficients over a wide frequency range according to the arrays of perforated plates with different values of G and a. We found that the wave absorbing system using the arrays of upright perforated plates is sufficient to install in the ocean engineering basin.

• 대기
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• 제16권4호
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• pp.303-318
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• 2006

A parameterization of gravity wave drag induced by cumulus convection (GWDC) proposed by Chun and Baik is implemented in the KMA operational global NWP model (GDAPS), and effects of the GWDC on the forecast for July 2005 by GDAPS are investigated. The forecast result is compared with NCEP final analyses data (FNL) and model's own analysis data. Cloud-top gravity wave stresses are concentrated in the tropical region, and the resultant forcing by the GWDC is strong in the tropical upper troposphere and lower stratosphere. Nevertheless, the effect of the GWDC is strong in the mid- to high latitudes of Southern Hemisphere and high latitudes of Northern Hemisphere. By examining the effect of the GWDC on the amplitude of the geopotential height perturbation with zonal wavenumbers 1-3, it is found that impact of the GWDC is extended to the high latitudes through the change of planetary wave activity, which is maximum in the winter hemisphere. The GWDC reduces the amplitude of zonal wavenumber 1 but increases wavenumber 2 in the winter hemisphere. This change alleviates model biases in the zonal wind not only in the lower stratosphere where the GWDC is imposed, but also in the whole troposphere, especially in the mid- to high latitudes of Southern Hemisphere. By examining root mean square error, it is found that the GWDC parameterization improves GDAPS forecast skill in the Southern Hemisphere before 7 days and partially in the Northern Hemisphere after about 5 days.

• 항공우주시스템공학회지
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• 제14권4호
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• pp.18-24
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• 2020

The counter-flow jet from a supersonic/hypersonic vehicle causes a structural change in the shock wave generated around the aircraft, which can lead to reduced drag and heat loads. Since the idea is to mount a counter-flow jet device for drag reduction in the aircraft, it is necessary to understand the effect of such a device on the entire aircraft. In this study, the effect of drag reduction due to counter-flow jet on a conventional rocket configuration was analyzed through CFD analysis. The results showed that the drag reduction effect was the largest in the blunt region and that the counter-flow jet also affected the downstream of the aircraft. The analysis indicated that the drag reduction effect by the counter-flow jet was about 10 to 25 % when targeting the entire rocket-shaped area, while the effect was as high as 50% when targeting only blunt objects.

• 한국해양공학회지
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• 제22권3호
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• pp.18-23
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• 2008

This study investigated interactions between the internal-external wave field of a permeable coastal structure consisting of rubble. The study examined the application criteria of an existing numerical model (CADMAS-SURF V.4.0) and proposed a modified method to provide reasonable results. In particular, the study focused on and emphasized the water surface profiles in front of a structure, wave run-up/run-down on a slope, and internal water level fluctuations due to the drag coefficient and porosity of a rubble mound structure. In conclusion, the result show that when the vertical fluctuations of the internal water levels in permeable coastal structures exhibited high-quality representation. Sane responses can be seen for wave run-up/run-down characteristics on its slopes.

• 한국습지학회지
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• 제18권1호
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• pp.84-93
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• 2016

해양과 육지 사이에 있는 연안습지는 연안의 수질을 개선하고 다양한 생물의 자연적인 서식처로 이용될 뿐 아니라 연안침식을 억제하는 기능을 가지고 있다. 연안식생은 외해에서 입사하는 파에너지 또는 폭풍해일을 감소하며 해저 안정화를 통해 습지를 유지하는 기능을 가지고 있다. 식생에 의한 파랑감쇠의 특성을 위해서는 식생과 파랑의 역학적 과정의 검토가 필수적이며 이를 통해 연안과정이나 연안의 동수역학적 특성을 이해할 수 있다. 본 연구에서는 파랑조건 이외에 식생형태에 따른 파랑감쇠 특성을 정량화하기 위해 수리실험을 통해 검토하였으며, 식생모형은 강성식생을 대상으로 규칙파가 작용하는 경우에 대해 파악하였다. 파형경사 ak와 상대수심 kh에 따른 수면위로 돌출된 식생에 대한 파랑감쇠를 검토하기 위하여 수리실험과 수치해석을 수행하였다. 실험결과에 대한 파고감쇠는 Dalrymple et al.(1984)의 파고감쇠식을 통해 식생에 의한 파고전달율, 감쇠율 및 항력계수를 해석하였다. 실험결과 식생에 작용하는 항력계수는 Reynolds수 보다는 Keulegan-Carpenter 수와 상관성이 있고, 파형경사가 증가할수록 파고감쇠율이 증가하고 있음을 확인하였다.

• 한국가시화정보학회지
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• 제17권1호
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• pp.34-42
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• 2019

Aerodynamic characteristics for a launch vehicle are numerically analyzed with various conditions. The local drag coefficients are high at the nose of the launch vehicle in subsonic region and on the main body in supersonic region because of the induced drag and the wave drag, respectively. The drag coefficients show the similar trend with the angle of attack except zero degree. However, the more the angle of attack increases, the more dependent on the Mach number the lift coefficient is. The body rotation for the flight stability destroys the vortex pair formed above the body opposite to the flight direction, so the flow fields are more or less complicated. The drag coefficient of the launch vehicle at sea level is about three times larger than that at altitude 7.2 km. And the thrust jet at the nozzle causes to reduce the drag coefficient compared with the jetless transonic flight.