• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.12
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• pp.1097-1106
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• 2011

Unsteady numerical analysis was performed to simulate air-launched missiles from a complete helicopter in hover by using an unstructured overset mesh flow solver coupled with a module of six degree-of-freedom motion of equations. The unsteady computations have been performed to obtain flow fields around the complete helicopter including main rotor, tail rotor, and fuselage equipped with multiple missiles, and six-DOF simulation has been performed to predict the behavior of the air-launched missile. The effects of the launching position and the missile thrust on the trajectory of the missile were investigated as well as the aerodynamic interference of the air-launched missile under the unsteady downwash produced by main rotor.

• Journal of computational fluids engineering
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• v.13 no.1
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• pp.49-56
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• 2008

Chimera grid methods have been widely used in Computational Fluid Dynamics due to its simplicity in constructing grid systems over complex bodies, and suitability for unsteady flow computations with bodies in relative motion. However, the interpolation procedure for ensuring the continuity of the solution over overlapped regions fails when the so-called orphan cells are present. We have adopted the MLS(Moving Least Squares) method to replace commonly used linear interpolations in order to alleviate the difficulty associated with the orphan cells. MLS is one of the interpolation methods used in mesh-less methods. A number of examples with MLS are presented to show the validity and the accuracy of the method.

• 한국전산유체공학회:학술대회논문집
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• 2010.05a
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• pp.341-346
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• 2010

In this paper, viscous flow calculation of pump-jet that is used as underwater propulsor was made by using RANS equation. For the validation, calculation for DTRC4119 marine propeller was made and reasonable agreements were obtained between the present results and the experiment. An unstructured overset mesh technique is used for analysis of relative motion between rotor and stator in pump-jet propulsor. Results for pump-jet propulsor were compared with computational results of another researcher.

• Journal of computational fluids engineering
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• v.5 no.2
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• pp.9-19
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• 2000

Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using the two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'Dynamic Domain Dividing Line' which has an advantage for constructing a well-defined hole-cutting boundary. A conservative Chimera grid method with the dynamic domain-dividing line technique is applied and validated by solving the flowfield around a circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver are also examined by computations of an oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.

• 한국전산유체공학회:학술대회논문집
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• 2007.04a
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• pp.17-22
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• 2007

Chimera grid Method is widely used in Computational Fluid Dynamics due to its simplicity in constructing grid system over complex bodies. Especially, Chimera grid method is suitable for unsteady flow computations with bodies in relative motions. However, interpolation procedure for ensuring continuity of solution over overlapped region fails when so-call orphan cells are present. We have adopted MLS(Moving Least Squares) method to replace commonly used linear interpolations in order to alleviate the difficulty associated with orphan cells. MSL is one of interpolation methods used in mesh-less methods. A number of examples with MLS are presented to show the validity and the accuracy of the method.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.1-10
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• 2002

Flow computations around forward sweep wing small aircraft have been conducted in this study. The main-wing of the forward-wing small aircraft is composed of two planforms: the inboard wing section with backward sweep angle which is known as strake and the outboard wing section with forward sweep angle. The geometrical discontinuity or kink generated by the combination of these two different planforms requires detailed flow analysis around wing. Four different solvers were used to calculate aerodynamic data and the accuracy of each method is examined. For the convenience of grid generation over the aircraft geometry, the overset grid method was applied. Through this calculation, the basic aerodynamic data of the forward-wing aircraft were provided and the aerodynamic characteristics of the wing is expounded.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.74-81
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• 2011

A numerical simulation is performed to study the ground effect of a rotating rotor blade on a whirl tower using unstructured overset mesh. The aerodynamic change of the rotor blade by the structure around the whirl tower is also considered. The calculated results showed good agreement with the experiment for the hover performance. The ground effect of the rotor blade is investigated by comparing with the calculated results for the out of ground condition and the results of an analytic model.

• Journal of Broadcast Engineering
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• v.2 no.1
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• pp.36-44
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• 1997

We propose 3D perspective display using elevation matrix data with 2D information overlay. This algorithm is based on ID scan-line method and we used color index of the newly developed raster map, VRRG(Vector Restored Raster Graphics). The proposed method allows the fast generation of perspective view of 3D data with 2D overlay and the fast selective display of the features of 2D overlay.

• Proceedings of the Korea Water Resources Association Conference
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• 2021.06a
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• pp.71-71
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• 2021

현재 국내에서 사용되고 있는 지자체 단위 위험도 평가 기법들은 자연재난과 사회재난으로부터 유발되는 여러 위험성들을 함께 고려하여 평가에 반영하고 있다. 또한, 지자체 내에서 홍수위험에 노출될 수 있는 대상만을 선별하여 분석한 것이 아닌 지자체별 단순 통계값으로 평가가 이루어지기 때문에 홍수위험에 대한 정확한 평가가 어렵다는 한계를 가지고 있다. 따라서 본 연구에서는 Indicator Based Approach(IBA)에서 제시하는 평가 항목인 Hazard, Exposure, Vulnerability, Capacity 중 Exposure에 해당하는 건축물수를 대상으로 홍수위험지도와 중첩되는 건축물들을 선별하여 홍수위험도 평가를 수행하였다. 지자체별 건축물수 산정은 2018년 11월 기준 경기도 31개 시군별 도로명주소 전자지도(건물)와 500m × 500m 건축물수 격자자료를 사용하였다. 건축물수 격자자료는 도로명주소 전자지도의 건물 폴리곤 자료 대비 분석이 간편하다는 장점을 가지고 있다. 비교 분석을 통해 공간분석자료의 유형에 따라 발생하는 통계값의 차이는 격자자료에 보정계수를 적용하여 보완하였다. 보정된 경기도 지자체별 건축물수 격자자료로 세부지표 지수를 산정한 결과 단순히 자지체별 건축물수를 사용했을 때에는 화성시, 용인시, 평택시 순으로 지수가 크게 산정되었다, 하지만 홍수위험지도와 중첩된 건축물수를 사용했을 때에는 고양시, 광명시, 김포시 순으로 지수가 크게 산정되었다. 본 연구를 통해서 건축물수 격자자료와 홍수위험지도를 사용하여 위험도 평가를 수행했을 때 기존 방법론 대비 합리적인 평가결과를 얻을 수 있었다.

• Journal of the Society of Naval Architects of Korea
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• v.56 no.1
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• pp.47-57
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• 2019

Recent CFD solvers in engineering have to treat geometrically complex domains and moving body problems. In ship hydrodynamics, flow around the stern and ship motions in waves are examples of such cases mentioned before. The unstructured grid scheme is successfully applied for these problems, but it has weakness of inefficient memory usage and intensive computational time as compared to the structured grid method. Overset grid scheme is one of the alternatives for structured grid system taking advantage of fast and memory efficiency. Overset grid scheme is especially useful for moving body problem because there is no need to re-mesh around the body. In this paper, we adopted the Suggar++, the grid connectivity and interpolation utility for the overlapping grid, to WAVIS which is the in-house flow solver of KRISO. Then we introduced some applications using the overset grid method for flow analysis around the ships. The computed results show that WAVIS with Suggar++ is practically feasible and has an advantages for moving geometry cases.