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산불 열영향 범위 산정을 위한 실험 및 FDS 데이터 비교
김형식 ( H S Kim ),강영진 ( Y J Kang ),김장환 ( J H Kim ),김경하 ( K H Kim ),이병두 ( B D Lee ),김정훈 ( J H Kim ) 한국안전학회(구 한국산업안전학회) 2014 한국안전학회지 Vol.29 No.4
This research deals with the combustion experiment of pine trees, which are the most representative species in Korea. Experimental data are compared with theoretical ones using Fire Simulation Program(FDS). It is considered that horizontal/verticaltemperature distribution and radiant heat influence on adjacent areas in fire scenes. The linear function for separation distance totemperature was drawn by applying Stefan-Boltzmann``s law; y=112.13133×(σT4)-0.52916 for calculating the separation distance. Incombustion experiment, the radiant heat came to 1.4∼1.5kW/㎡ in case of the separation distance by one meter. The numerical valuesmean that human body show the critical level of pain after one minute without a protective equipment.
강영진(Y.J. Kang),양영록(Y.R. Yang),김성현(S.H. Kim),황의창(U.C. Hwang),염용일(Y.I. Youm),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.11
In this study the performance of the nozzle of a rocket system is evaluated using a CFD code. The main emphasis of the investigation is placed on the effects of the number (9 and 12) and the depth of fluted edge in the rocket nozzle. It is observed that as the depth increases the rolling moment of the nozzle increases while the thrust of the nozzle decreases.
강영진(Y.J. Kang),양영록(Y.R. Yang),황의창(U.C. Hwang),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2011 한국전산유체공학회지 Vol.16 No.3
As a preliminary design study to achieve target aerodynamic performance, this work was conducted on an original nozzle with 9 flutes in order to design a fluted nozzle with 12 flutes. The thrust and rolling moment of the nozzle with 12 flutes were analyzed using a CFD code according to the depth and rotation angle of the flutes. Based on this, a fluted nozzle with 12 flutes was optimized to yield the same thrust as that of the original nozzle with 9 flutes. The response surface method was applied for shape optimization of the fluted nozzle and design variables were selected to determine the depth angle and rotation angle of the flutes. An optimized shape that led to a thrust as strong as that of the original nozzle was obtained
Winglet이 부착된 날개의 구조변형에 의한 공력 변화
이영민(Y.M. Lee),강영진(Y.J. Kang),정성기(S.K. Jung),명노신(R.S. Myong),조태환(T.H. Cho) 한국전산유체공학회 2009 한국전산유체공학회 학술대회논문집 Vol.2009 No.4
The aerodynamic characteristics of aircraft winglet with structural deformation was investigated using the static FSI(Fluid-Structure Interaction) system. The system, comprised of CAD, CFD, CSD, VSI, and grid regeneration modules, was constructed. In the process VSI, grid regeneration, and integration modules were developed to combine CSD and CFD modules. As a test model, KC-135A, the double winglet suggested by Whitcomb, was selected and its aerodynamic characteristics for the rigid and deformable models was calculated by applying the static FSI system. As a result, the lift and drag coefficients of test models were reduced to 11% and 1.3%, respectively.
피토튜브 장착위치 선정을 위한 전진 비행하는 헬리콥터 유동장의 CFD 분석
조현구(H.G. Cho),강영진(Y.J. Kang),김성현(S.H. Kim),명노신(R.S. Myong),조태환(T.H. Cho),박영민(Y.M. Park) 한국전산유체공학회 2008 한국전산유체공학회 학술대회논문집 Vol.2008 No.-
A CFD analysis of helicopter flowfield in forward flight is considered as non-trivial issue because of the complexity of vorticity-dominated flowfield. In this work, a study on the selection of the proper location for the installation of the Pitot probe is conducted using a CFD code which can deal with the interaction of rotor blade vortex and body. To describe the flow patterns for rotating rotor blades and body, the sliding mesh scheme is utilized. Pressure distributions and flow patterns are also analyzed to identify regions free from the interaction of body and wake induced from rotor blades.