• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.952-962
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• 2015

Various types of altitude compensation nozzles have been investigated to develop an effective propulsion system. In order to obtain baseline data for future study of dual bell nozzles, main characteristics and key parameters of dual bell nozzles are summarized and described by analysing DLR dual bell nozzles. DLR's experimental researches show that inflection angle is proportional to transition NPR, and extension length is proportional to side load, but inversely proportional to transition NPR and transition duration. Therefore, the nozzle geometry can be determined through the performance prediction process and thus the optimization process is required to meet performance requirements between parameters.

• Journal of the Korean Institute of Gas
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• v.20 no.3
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• pp.1-11
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• 2016

Production data from hydraulically fractured well in coalbed methane (CBM) reservoirs was analyzed using decl ine curve analysis (DCA), flow regime analysis, and flowing material balance to forecast the production performance and to determine estimated ultimate recovery (EUR) and timing for applying the DCA. To generate synthetic production data, reservoir models were built based on the CBM propertie of the Appalachian Basin, USA. Production data analysis shows that the transient flow (TF) occurs for 6~16 years and then the boundary dominated flow (BDF) was reached. In the TF period, it is impossible to forecast the production performance due to the significant errors between predicted data and synthetic data. The prediction can be conducted using the production data of more than a year after reached BDF with EUR error of approximately 5%.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.54-61
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• 2014

In this study, a plume exhausted from rocket nozzle is investigated by using an unstructured 2-dimensional axisymmetirc DSMC code at various altitude. The small back-pressure to total-pressure ratio($P_b/P_o$) and large $P_b/P_o$ represent low and high altitude condition, respectively. At low altitude, the plume shows a typical complicated structure (e.g. Mach disk) of underexpanded jet while the high altitude plume experiences plain expansion. The various features of exhaust plume is discussed including density, translational/rotational temperature, Mach number and Knudsen number. The results shows that even at 20 km altitude where the freestream Knudsen number is small as $1.5{\times}10^{-5}$, the transitional and rarefied flow regimes can occur locally within the plume. It confirms the necessity of DSMC computation at low altitude.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1993.04b
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• pp.310-314
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• 1993

본 연구에서는 전기유동체의 전기장 부하 변화에따른 역학적특성을 고찰하였다. 유체에 가해지는 전기장은 0 .approx. 2.5 kV/mm 까지 변화시켰고, 외부에서 가해지는 회전력은 0 .approx. 500 rpm 까지의 범위로 하였으며, 용매의 종류를 달리하고 각각의 용매에 대한 중량비를 달리하여 자체 조성한 5종류의 전기유동유체에 대하여특성 고찰하였다. 각각의 전기유동유체는 부하되는 전기장에 대하여 전단력과 전단비의 관계가 선형적으로 증가하였고, 전기유동유체의 항복응력도 부하되는 전기장의함수로 증가함을 알 수 있었다. 또한 부하되는 전기장의 크기뿐만 아니라 입자의 중량비, 용매의 종류도 전기 유동유체의 역학적 특성에많은 영향을 미침을 알 수 있었다.

• Transactions of the Korean Society of Mechanical Engineers
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• v.13 no.6
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• pp.1128-1146
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• 1989

본 논문에서는 2상 횡유동의 진동 메카니즘을 규명하기 위한 실험계획의 일환으로 실시된 실험으로 부터 튜브집합체의 추가질량(hydrodynamic mass)과 감쇠 (damping)에 대해 고찰하였다. 실험은 튜브배열과 피치 대 직경비(pitch-over-di- ameter:.rho./ｄ)가 상이한 튜브집합체에 대해 2상 유체를 모의한 공기-물(air-water) 혼합물에서 수행하였다. 액체상태로부터 99%의 보이드율까지 변화된 2상 유체의 유량은 튜브가 유체탄성 불안정성 (fluidelastic instability)에 도달할 때까지 점진적으로 증가하였다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.22 no.6
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• pp.757-770
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• 1998

A Navier-Stokes code with a low Reynolds number k-.epsilon. turbulence model was tested to investigate its predictability for the unsteady transitional boundary layer flow due to rotor-stator interaction. A preliminary calculation with three different numbers of time steps 300, 600, and 1000 for a rotor wake passing period was carried out to see the effects of time steps on the unsteady flow and pressure fields due to rotor-stator interaction. Numerical solutions showed that unsteady pressure was much more sensitive to the number of time steps and over 600 time steps should be used to get a numerical solution independent of the number of time steps for a rotor wake passing period. The original low Reynolds number k-.epsilon. turbulence model showed very poor prediction of the unsteady transitional boundary layer flow due to rotor-stator interaction. This was due to the excessive production of turbulent kinetic energy near the leading edge. A modification suggested by Launder was incorporated and the modified model captured well the wake induced transitional strip. Present solutions also showed improved prediction over previous Euler/boundary layer solution in terms of the onset of unsteady transition and its extent.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.22 no.6
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• pp.771-787
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• 1998

A Navier-Stokes code with a modified low Reynolds number k-.epsilon. turbulence model was used to study the unsteady transitional boundary layer flow due to rotor-stator interaction. The modification, proposed by Launder, to improve prediction of stagnation flows was incorporated to the low Reynolds number k-.epsilon. turbulence model by Fan-Lakshminarayana-Barnett. Numerical solution is shown to capture well the calmed laminar flow as well as the wake induced transitional strip due to rotor-stator interaction and shows improvement, in terms of onset of transition and its length, over previous Euler/boundary layer solution. The turbulent kinetic energy shows local maximum along the upstream rotor wake in the wake induced transitional strip and this characteristics is observed untill the end of transition. The wake induced strip also shown apparent even in the laminar sublayer as the upstream rotor wake penetrates inside the boundary layer.

• Proceedings of the Korea Committee for Ocean Resources and Engineering Conference
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• 2006.11a
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• pp.426-426
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• 2006

선박이 천 흘수 및 수로를 운항하는 경우 바닥과 벽면의 영향으로 인해 선체침하 및 비대칭적인 힘이 선체 주위에 발생하여 바닥이나 다른 선박 혹은 수로의 벽에 충돌하는 현상이 발생한다. 특히, 수로가 많은 유럽이나 북미를 운항하는 해운회사와 항해사들은 선박의 충돌을 방지하기 위해서 중요한 문제로 다루고 있다. 따라서, 본 연구에서는 선박의 안전한 항해를 위해 수치해석을 이용하여 선박과 벽면 사이에 발생하는 유체역학적 힘, 즉 Sway force와 Yaw Moment를 정성적으로 추정하고자 하였다. 천 흘수 유동 해석용 프로그램을 작성하였으며, 검증을 위해서 Wigley 선형에 적용하여 h/T별로 계산을 수행하여 시험결과와 비교하였다. 그리고, 벽면효과를 해석 할 수 있는 프로그램을 작성하여 실적선인 원유운반선 2척에 대하여 3가지 파라메터, 즉 선속, 수심 그리고 선박과 벽면 사이 거리의 변화에 따른 다양한 계산을 수행하였다. 계산된 결과는 시험결과 및 기 발표된 수치해석 결과와 비교하였다. 기 발표된 논문에서는 시험결과와 계산결과가 상이한 결론을 보여 주었는데, 그 이유는 수치해석에 있어서 자유표면 문제를 선형화된 자유표면 조건식을 사용한 부분을 가장 큰 이유로 언급하였다. 하지만, 본 연구의 결과는 Sway force와 Yaw Moment가 기 발표된 논문의 시험결과와 정성적으로 일치함을 보여 주었다. 본 연구를 통해 수치해석 방법으로 선박에 작용하는 비대칭 유동에 대한 유체역학적인 힘을 정성적으로 추정할 수 있었고, 제한된 수로에서 선박의 조종성 예측 및 수로 설계시 유용한 정보를 제공할 수 있을 것이라고 판단되어 진다.

• 한국전산유체공학회:학술대회논문집
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• 2009.04a
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• pp.87-89
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• 2009

In the present paper, transition turbulence model is applied to the NACA64(3)618 and detailed flow features are studied. The turbulence model is sensitive to the boundary layer grid quality and y+ of the grid was limited to 1. The prediction of the transition region is dependent on the local flow condition. The pressure coefficient distribution of the transition turbulence model is compared with that of the fully turbulent mode and the drag distribution of the transition turbulence model was compared with that of the wind tunnel test.

• The KSFM Journal of Fluid Machinery
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• v.10 no.5
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• pp.27-33
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• 2007

Rarefied gas flows through two-dimensional micro channels are studied numerically for the performance optimization of a nanomembrane-based Knudsen compressor. The effects of the wall temperature distributions on the thermal transpiration flow patterns are examined. The flow has a pumping effect, and the mass flow rates through the channel are calculated. The results show that a steady one-way flow is induced for a wide range of the Knudsen number. The DSMC(direct simulation Monte Carlo) method with VHS(variable hard sphere) model and NTC(no time counter) techniques has been applied in this work to obtain numerical solutions. A critical element that drives Knudsen compressor Is the thermal transpiration membrane. The membranes are based on aerosol or machined aerogel. The aerogel is modeled as a single micro flow channel.