• Journal of The Korean Society of Agricultural Engineers
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• v.54 no.5
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• pp.1-7
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• 2012

본 연구의 목적은 국내에서 상용되고 있는 온실 피복재 및 보온재의 조합에 따른 관류열전달계수를 핫박스를 이용하여 평가하는 것이다. 온실용 일중 및 이중 피복재와 이중 보온재의 조합에 대하여 야간천공복사 차단여부에 따른 관류열전달계수를 핫박스를 이용하여 실외에서 측정하였다. 처리조건은 일중피복, 이중피복, 이중피복과 이중 마트보온재 및 이중피복과 이중 다겹보온재의 조합조건과 천공복사 유무에 따른 조건이며 총 8가지이다. 제작된 핫박스는 상시 변화하는 외부의 기상조건하에서도 내부온도를 설정된 온도로 일정하게 잘 유지할 수 있었다. 온실 피복재 및 보온재의 관류열전달계수를 측정하는 실내용 측정장치는 반드시 야간천공복사를 모의할 수 있는 측정장치가 되어야 할 것이다. 야간복사를 차단함으로서 온실의 열 손실을 줄여 보온효과를 얻을 수 있을 것으로 분석되었다. 모든 피복방식에 대해 야간복사 차단장치 유무에 관계없이 높은 풍속에서의 관류열전달계수가 낮은 풍속에서보다 더 큰 것으로 나타났다. 본 연구에서 사용된 측정기법을 사용하면 국내에서 생산되는 피복재 및 보온재의 관류열전달 특성을 정량적으로 비교할 수 있을 것으로 기대된다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.16 no.3
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• pp.1605-1610
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• 2015

The present study has been accomplished to elucidate the effect of radiation heat transfer in the heat transfer analysis of refrigerator gasket, which has near 30% of refrigerator heat loss. The numerical heat transfer analysis has been conducted with the simplified modeling of refrigerator gasket. From the present CFD analysis, heat loss at the gasket is $25.6W/m^2$ for the case without radiation effect and that for the case with radiation effect is $55.0W/m^2$, which is 2.2 times greater heat loss. The radiation protection layers were installed in the gasket from 0 to 7 and the case with 7 layers has 33% reduction effect of heat loss compared with the case without any radiation protection layer. Additionally, it is better effect of radiation heat loss reduction that the radiation protection layers would be placed to the outer or inner side of gasket rather than placing to the center of gasket.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.85-91
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• 2005

Radiative heating of a liquid rocket base plane due to plume emission is numerically investigated. Calculation of flow and temperature fields around rocket nozzle precedes and thereby realistic plume shape and temperature distribution inside the plume are obtained. Based on the calculated temperature field, radiative transfer equation is solved by discrete ordinate method. With the sample rocket plume, the averaged radiative heat flux reaching the base plane is calculated about 5 kw/m$^{2}$ at the flight altitude of 10.9 km. This value is small compared with radiative heat flux caused by constant-temperature (1500 K) plume emission, but it is not negligibly small. At higher. altitude (29.8km), view factor between the base plane and the exhaust plume is increased due to the increased expansion angle of the plume. Nevertheless, the radiative heating disappears since the base plane is heated to high temperature (above 1000 K due to convective heat transfer.

• Solar Energy
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• v.15 no.3
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• pp.39-52
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• 1995

This study is investigated numerically on the heat transfer characteristics of surface radiation-natural convection interactions in a two dimensional enclosure assumed Ondol cavity. Mean Nusselt number of the bottom surface with surface radiation is increased by increasing wall emissivity and by decreasing dimensionless thickness of adiabatic wall. and is greater than that without radiation. Mean Nusselt number of the bottom surface for convection only with surface radiation is slightly smaller than that without surface radiation with decrease dimensionless thickness of adiabatic wall.

• Fire Protection Technology
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• s.25
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• pp.13-18
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• 1998

• Journal of the KSME
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• v.49 no.9
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• pp.28-34
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• 2009

이 글에서는 열광기전 에너지 변환에 대한 대략적인 설명과 열광기전 시스템의 장단점, 그리고 열광기전 성능 개선을 위한 마이크로/나노 스케일에서의 복사열전달 연구에 대해 소개한다.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.17-25
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• 2009

The precise calculation of gas absorption coefficient in the radiative transfer equation is very important to the prediction of radiative heat transfer induced from liquid engine plume in view of base insulation design. For this purpose, the WNB model for gas absorption coefficient is described with the selection of important parameters and then the calculated results are compared with those of SNB model for validation. Total emissivity, narrow band averaged intensity and total intensity are calculated and compared to the results of SNB model. As results, the total emissivity and the total intensity are well matched within 3.1% and roughly 5 % error, respectively. Moreover, the gas modeling database is constructed with estimation of the combustion gas composition of $CO_2$ and $H_2O$ for liquid engine plume.

• Journal of Energy Engineering
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• v.15 no.4 s.48
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• pp.250-255
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• 2006

In this study, the discrete ordinates method which has been widely used in the solution of neutron transport equation is applied to the solution of the time dependent radiative transfer equation. The self-adjoint form of the second order radiation intensity equation is used to enhance the stability of the solution, and a new multi-step linearization method is developed to avoid the nonlinearity in the material temperature equation. This new solution method is applied to the well known Marshak wave problem, and the numerical result is compared with that of the conventional Monte-Carlo method.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.2
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• pp.31-38
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• 2006

A study of thermal characteristics of the airship considering radiation heat transfer has been conducted by building a numerical model for the airship in order to identify the possibility to obtain the reliable flight performance in severe stratospheric heat conditions. The variations of distributed temperature of the skin and the inner flow by free convection have been calculated according to the change of the solar position. As the results of the analyses, the stratospheric heat conditions slightly have an influence on the flight performance of the airship.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.4-4
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• 1998

고체 추진제의 비정상적인 연소 현상을 해석하여 연소 불안정을 예측하는 것은 추진시스템의 설계 시 매우 중요하다. 로켓의 비정상 연소 현상을 해석하기 위하여 많은 이론적 연구가 진행되어 왔다. 이론적인 해는 주로 선형 해석의 결과들로 정상 상태에서 발생하는 불안정 현상을 예측하는 데에는 적합하지만 비정상 현상을 설명하기에는 부족하다. 따라서 수치 기법을 이용한 비선형 해석이 수행되어 졌다. 기존의 비정상 연소에 관한 연구들은 일정한 물성치를 사용하고 추진제 내에서의 화학 반응과 복사 열전달 등을 무시하여 추진제의 특성을 단순화 시켜 비정상 해석을 수행하였다. 본 연구에서는 비정상 연소 현상에 대한 비선형 수치 해석을 하려한다. 실험에서 밝혀진 것과 같이 추진제의 물성치를 온도의 함수로 사용하고 응축영역으로의 복사 열전달을 고려하였다.