• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.955-965
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• 2010

The MH-75 propeller for the MAV propulsion is designed using a free vortex design method which considers design parameters such as the hub-tip ratio, the twist angle distribution, the maximum camber location and the chord length of the propeller blade. Aerodynamic characteristics of the MH-75 propeller are predicted by changing the flight speed using the frequency domain panel method. And, the thrust characteristics of the MH-75 propeller are measured using the balance system of the subsonic wind tunnel for the validation of numerical results. The performance characteristics of the MH-75 propeller satisfied with design requirements. Numerical results of the MH-75, which are predicted by the frequency domain panel method, are more agree with experimental results compare with XFOIL.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.6
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• pp.31-38
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• 2005

Aerodynamic influence coefficient linearly relates pressure with downwash in panel method for load analysis in which the viscosity of a flow is ignored and the compressibility cannot be taken into account in transonic region. Since the planform of an aerodynamic surface determines the coefficient, the panel method has a limit to the analysis of low Reynolds number flow. The accuracy of the pressure distribution can be improved by a direct correction to the pressure or a correction to the downwash, which is considered the change of camber or thickness, using the aerodynamic coefficients from wind tunnel test as constraints. A premultiplying correction method as well as a postmultiplying correction method is applied to a micro air vehicle to provide more accurate aerodynamic pressure for trim and load analyses. Theoretical aerodynamic pressure is obtained from the panel method. Correction factor matrix and correct pressure coefficient are computed for the conditions with two constraints in addition to single constraint. The postmultiplying correction method gives a better improvement in pressure distribution on micro air vehicle due to the flow characteristics on it.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.6
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• pp.1-7
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• 2003

In this study, steady/unsteady aerodynamic characteristic for three dimensional symmetric wing was investigated numerically using Vortex Panel Method. This program utilized linearly varying vortices in x and y directions distributed on the wing surface and was applied to the incompressible potential. flow around a three dimensional wing Separation and deformation of the wake are not considered. The comparison between NACA Airfoil Data and the computed results showed excellent agreement. πus method was applied to unsteady wings undergoing both sudden pitch-up and constant rate pitching motion. In the unsteady flow analysis, a formation and a time-dependent locations of Starting Vortices are considered and the effect of Starting Vortices on aerodynamic characteristic of the wing was calculated. The present method can be extended to apply for more complicated cases such as pitching, flapping and rotating wing analysis.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.11a
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• pp.57-60
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• 2011

EPS패널의 열방출율과 가스유해성에 대한 연구는 꾸준히 진행되어왔다. 그러나 그 동안의 시험 결과는 KSF ISO 5660-1(콘칼로리미터) 시험규정에 의한 소형시편을 이용한 것으로 난연제의 과다투입 또는 심재의 변형이 쉬워 결과를 신뢰하기 힘들고 실제 생산되는 크기의 샌드위치패널의 난연성능을 판단하기 힘들다. 따라서, 보다 정확한 실물화재시험의 필요성이 요구되고 있다. 난연 EPS샌드위치패널과 일반EPS샌드위치패널의 실물화재 실험결과 난연EPS샌드위치패널은 기타재료의 샌드위치패널과 열방출율, 연기발생율, 부분별 온도분포, 플래시오버등과 같은 난연성능이 EPS샌드위치패널과 우레탄폼패널보다 우수하며, 글라스울과 비슷한 성능을 나태내는 것을 확인 할 수 있다. 그래서 시공성, 경제성 등의 EPS샌드위치패널의 장점을 그대로 유지하며 난연제의 코팅법을 통해 우수한 난연성능을 확보하였다.

• Journal of the Society of Naval Architects of Korea
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• v.29 no.4
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• pp.66-74
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• 1992

A panel method in the spirit of Hess & Smith(1962), and also of Dawson(1977) was developed to compute the wave resistance of a submerged, or a surface piercing, body moving in the water of finite depth. As a boundary condition on the free surface what is called the Poisson equation is used, while Yasukawa(1989) chose the Dawson equation for which the double-body flow is regarded as the basic one. In order to satisfy the boundary condition on the bottom surface automatically, the sum of a Rankine source and its image with respect to the bottom surface is chosen as the Green function, and hence the singularity is distributed only on the body and on the free surface thereby decreasing the required number of panels dramatically, compared to that of Yasukawa, without the consequential loss of accuracy. Calculations were done for a submerged sphere and for the Wigley hull, and the results are compared with other existing analytical and numerical data.

• Journal of the Society of Naval Architects of Korea
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• v.30 no.1
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• pp.73-86
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• 1993

This paper describes a potential-based panel method for the prediction of steday performance of a marine propeller operating in a uniform oncoming flow. An integral equation with unknown dipole strengths is formulated by distributing the normal dipoles and/or sources on the blade and hub surfaces and the wake sheet, and is solved numerically upon discretization. A hyperboloidal panel has been adopted to compute the potential induced by a normal dipole on a non-planar quadrilateral panel. The Kutta condition is satisfied by iteratively annulling the pressure jumps at the trailing edge. Extensive convergence tests are carried out, and the influence of the wake model upon performance is studied. Predicted performance is shown to correlate well with the experiments.

• Journal of the Society of Naval Architects of Korea
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• v.38 no.4
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• pp.11-22
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• 2001

The interaction between forward mounted propeller and wing in ground effect, and its aerodynamic performance are analyzed by potential flow approximation. A Vortex Lattice Method(VLM) for the propeller analysis and a potential based panel method for the WIG are used together with an image method by assuming the free surface as a rigid wall. The interaction of propeller and wing in the proximity of the ground is taken into account by an iterative procedure where the boundary conditions are satisfied with the given convergence criteria. The program developed is first checked by comparing its numerical results with the experimental data and other numerical results for the propeller MP101-rudder MR21 system. Then, the propeller-WIG interaction and its performance versus ground clearance are investigated by changing parameters such as propeller position, diameter and speed of revolution. It is shown that the forward mounted propeller increases the lift forces of the wing and also enhances the height stability, depending on the design parameter. Therefore, the appropriate selection of the design parameter such as propeller diameter, revolution, the longitudinal and vertical position of propeller is necessary.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.942-944
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• 2017

High-speed vehicles are subjected to complex loads, such as acoustic pressure from the engine at launch and aerodynamic heating and aerodynamic pressure during flight. A thermal protection system panel is required to protect internal systems such as the fuel tank of the vehicle from the external environment. This study defines analytical models for heat transfer and thermal structure characteristics of the thermal protection system panel. Furthermore, the study performed parameters analysis to achieve the thermal structural integrity and to make it lighter.

• Proceedings of the Korea Water Resources Association Conference
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• 2012.05a
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• pp.415-415
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• 2012

유역의 홍수위험도를 평가하기 위하여 선행 연구로서 DPSIR framework를 적용한 인자를 선정하였다. 이때 인자의 범위를 사회적, 경제적, 환경적 분야로 구분하고 각 분야에 대하여 홍수로 인하여 야기되는 유역의 다양한 영향요소를 포함하여 인자를 선정하였다. 본 연구에서는 이를 대상으로 각 인자의 가중치를 선정하기 위하여 패널식 조사연구기법인 Delphi 방법을 적용하였다. Delphi 기법은 델파이 절차가 반복되는 동안 조사 참여자에게 전회의 조사 결과, 즉 통계적 집단 반응을 피드백하며 참여자는 이를 참고하여 자신의 판단을 수정 보완 할 수 있는 방법이다. 따라서 1차 설문조사를 통하여 각 패널은 홍수위험도 평가 인자에 대해서 주관적인 가중치를 선정하고 이를 분석한 결과를 피드백 받아 참고한 후 2차 설문조사에 응하여 가중치를 재선정하게 된다. 조사에 참여할 패널의 선정은 수자원분야의 전문가를 대상으로 하였다. 또한 각 인자에 대한 가중치를 수집하는 방법을 다양하게 설정하여 기법에 따른 영향을 검토하였다. 수집기법은 상대적 가중치 결정법 중에서 가장 많이 사용되는 순위법과 직접입력법, 절대적인 기준에 대한 가중치를 수집하기 위하여 Fuzzy 가중치 입력법을 사용하였으며 이 때 각 인자가 소속되는 분야와 DPSIR framework 요소에 대해서도 별도로 가중치를 수집하여 최종적인 인자의 가중치를 결정하였다. 본 연구는 추가 연구를 통해 남한강에 적용되며 인자의 자료는 문헌조사, 통계자료 조사 및 수리학적 수치모형 등의 분석을 통해 수집될 예정이다. 이를 통하여 사회, 경제, 문화, 환경적인 측면을 고려한 인자들을 반영한 하천의 구간별 상대적 홍수취약도를 정량적으로 제시할 수 있으며 하천 구간별 치수관리 우선순위를 결정하는데 적극적으로 활용될 수 있다.

• Journal of Ocean Engineering and Technology
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• v.25 no.4
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• pp.18-22
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• 2011

The Ranking source panel method was used to predict the flow phenomenon of a ship with a goose-neck type bulbous bow penetrating the free surface. The non-linearity of the free surface boundary condition was fully satisfied using an iterative calculation method, and the raised panel method was adopted to obtain a more stable solution at each iteration step. The panel cutting method was applied to generate a hull calculation grid at each iteration step, including the first step. At that time, the nose of the goose-neck type bulbous bow was divided by the free surface and the free surface panel was modified at each iteration step using the variable free surface panel method. Numerical calculations were performed to investigate the validity and efficiency of the applied numerical algorithm using the 3600 TEU container carrier. The computed wave resistance coefficients were compared with the experimentally achieved residual resistance coefficients.