• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 춘계학술대회논문집B
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• pp.555-560
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• 2000

An experimental study on pumping characteristics of various turbo-type drag pumps is purformed. The inlet pressures are measured for various outlet pressures of the test pump. The maximum compression ratios for nitrogen are 100,000(Disk-type drag pump+ turbo molecular pump), 10000(Helical-type drag pump+turbo molecular pump), 850 (Helical-type drag pump), 100(disk-type drag pump).

• Corrosion Science and Technology
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• 제7권5호
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• pp.283-287
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• 2008

The drag reduction agency (DRA) for gas pipeline, a novel method used for reducing friction or drag on a gas flowing to increase the transmission efficiency of gas pipeline, is a more flexible and economical technology than internal flow efficient coatings. In this paper, an effective DRA has been developed in Authors' Institute by analyzing the hydrodynamic friction resistance on internal gas pipeline and then studying the work mechanism and molecular structure of DRA. In the meantime, a group of property test for selecting DRA material has been determined, including viscosity, contact angle, volatility, corrosion, slab extending, and flow behavior in horizontal tube. The inhibition efficiency and drag reduction efficiency of the developed DRA have been investigated finally based on the relevant test methods. Results of corrosion test show that the developed DRA has very good inhibition effect on mild steel by brushing a thin layer of DRA on steel specimens, giving inhibition efficiency of 91.2% and 73.1% in 3%NaCl solution and standard salt fog environment respectively. Results of drag-reducing test also show that the Colebrook formula could be used to calculate friction factors on internal pipes with DRA as the Reynolds number is in the range of $0.75\times10^5\sim2.0\times10^5$. By comparing with normal industrial pipes, the friction resistance coefficient of the steel pipe with DRA on internal wall decreases by 13% and the gas flux increases by 7.3% in testing condition with Reynolds number of $2.0\times10^5$.

• 대한조선학회논문집
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• 제52권1호
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• pp.8-18
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• 2015

Reduction of the fuel oil consumption and corresponding greenhouse gas exhausted from ships is an important issue for today's ship design and shipping. Several concepts and devices on the superstructure of a container ship were suggested and tested in the wind tunnel to estimate the air drag reduction. As a preliminary performance evaluation, air drag contributions of each part of the superstructure and containers were estimated based on RANS simulation respectively. Air drag reduction efficiency of shape modification and add-on devices on the superstructure and containers was also estimated. Gap-protectors between containers and a visor in front of upper deck were found to be most effective for drag reduction. Wind tunnel tests had been carried out to confirm the drag reduction performance between the baseline(without any modification) configuration and two modified superstructure configurations which were designed and chosen based on the computation results. The test results with the modified configurations show considerable aerodynamic drag reduction, especially the gap-protectors between containers show the largest reduction for the wide range of heading angles. RANS computations for three configurations were performed and compared with the wind tunnel tests. Computation result shows the similar drag reduction trend with experiment for small heading angles. However, the computation result becomes less accurate as heading angle is increasing where the massively separated flow is spread over the leeward side.

• Journal of Mechanical Science and Technology
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• 제17권5호
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• pp.776-783
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• 2003

A low speed wind tunnel test was conducted for full-scale model of an unmanned aerial vehicle (UAV) in Korea Aerospace Research Institute (KARI) Low Speed Wind Tunnel(LSWT). The purpose of the presented paper is to illustrate the general aerodynamic and performance characteristics of the UAV that was designed and fabricated in KARI. Since the testing conditions were represented minor portions of the load-range of the external balance system, the repeatability tests were performed at various model configurations to confirm the reliability of measurements. Variations of drag-polar by adding model components such as tails, landing gear and test boom are shown, and longitudinal and lateral aerodynamic characteristics after changing control surfaces such as aileron, flap, elevator and rudder are also presented. To explore aerodynamic characteristics of an UAV with model components build-up and control surface deflections, lift curve slope, pitching moment variation with lift coefficients and drag-polar are examined. The discussed results might be useful to understand the general aerodynamic characteristics and drag pattern for the given UAV configuration.

• 한국항공우주학회지
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• 제33권9호
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• pp.9-15
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• 2005

국방과학연구소 풍동실험실에서는 회전익 항공기 개발에 소요되는 관련 풍동시험 기법의 확립과 형상연구 관련 시험자료의 확보를 위한 실험적 연구를 수행하였다. 본 연구는 회전익 항공기 동체구성품의 형상조합에 따른 항력증분과 안정성 평가를 위한 공기역학적 특성의 추출을 목적으로 하였으며, 풍동시험에는 모듈화된 1:8 축척의 회전익 항공기 동체형상과 500 rpm으로 회전하는 로터허브의 부분모형이 사용되었다. 시험결과들을 기존의 유사 항공기 시험결과들과 비교하였으며, 기존 연구결과들과 잘 부합됨을 확인하였다.

• 한국항공우주학회지
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• 제35권4호
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• pp.308-315
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• 2007

연구는 경비행기인 창공-91의 인증 획득을 위한 비행시험의 일부로서 상승성능을 파악하기 위하여 수행되었다. 창공-91은 1993년에 대한민국의 건설교통부로부터 최초로 인증을 취득한 단발엔진을 장착한 일반유형의 5인승 항공기이다. 상승을 위한 비행시험 절차 및 자료는 형식증명을 획득하는데 사용되었다. 톱니형 상승 데이터로부터 양항곡선방법으로 데이터를 처리하여 창공-91의 최대상승률, 최대상승각 속도, 최대상승률 속도, 그리고 절대상승한도를 구하였다. 또한, 상승성능의 결과로부터 양항곡선식을 구함으로써 형상항력계수와 오스왈드 효율계수를 비행기 설계시의 값과 비교하였다.

• 한국산학기술학회논문지
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• 제19권2호
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• pp.71-76
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• 2018

최근 도로시설물에 작용되는 하중을 저감시키기 위하여 다양한 기술이 개발되고 있으며, 그 중 풍하중 저감을 위한 유공판을 사용하는 기술이 일부 적용 중에 있다. 현재 국내 도로시설물 설계기준에서는 유공판의 항력계수에 대한 규정은 마련되어 있지 않다. 미국의 구조물 설계기준 'Minimum design loads for buildings and other structures'에서는 Letchford(2001)와 Giannoulis(2012)의 연구 내용을 바탕으로 건축물과 도로시설물의 유공판 항력계수 내용이 개정되었다. 본 연구에서는 유공판 항력계수 규정에 대한 준용 가능성을 분석하고자 관련 풍동실험을 수행하였다. 더불어 풍동실험 결과 값과 미국 설계기준의 항력계수 값을 비교 분석하였으며, 미국 설계기준 항력계수를 적용한 도로표지 지주 및 가로재의 부재 단면적 감소효과를 비교 분석하였다. 본 연구의 풍동 실험 결과 값과 미국 설계기준 값이 매우 유사한 수준으로 도출되었으며, 이에 따라 유공판 항력계수에 대한 준용이 가능할 것으로 판단된다. 항력계수 설계기준의 준용에 따른 유공형 도로표지 구조물의 단면적 감소효과 분석 결과, 지주는 약 9.45%, 가로재는 6.45%의 단면적이 감소하였다. 지주와 가로재를 합친 유공형 도로표지의 전체 구조물은 약 6.45%의 단면적 감소효과가 있는 것으로 나타났다.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2001년도 유체기계 연구개발 발표회 논문집
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• pp.203-208
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• 2001

In this paper, the pumping performance of the three-stage disk-type drag pump which works in the outlet pressure range from 4 to 0.01 Torr is studied experimentally. The rotational speed of the pump is 24,000rpm, and nitrogen is used as a test gas, The pumping characteristics of various drag pumps are investigated. The inlet pressures are measured for various outlet pressures of the test pump. The maximum compression ratios for zero throughput are measured for three-stage, two-stage BSC type, helical-type, one-stage BSC type and one-stage OSC type, respectively.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.577-580
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• 2002

In this paper, the pumping performance of the disk-type drag pump which works in the outlet pressure range from 4 to 0.001 Torr is studied experimentally. The pumping characteristics of various drag pumps are performed. The inlet pressures are measured for various outlet pressures of the test pump. The flow-meter method is adopted to calculate the pumping speed. Compression ratios and pumping speeds for the nitrogen gas are measured. The present experimental data show the leak-limited value of the compression ratio in the molecular transition region. The rotational speed of the pump is 24,000rpm. The inlet pressures are measured for various outlet pressures of the test pump. The ultimate Pressures for zero throughput are measured for three-stage, two-stage and single-stage disk-type, respectively.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.47-51
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• 2004

Accurate Prediction of a supersonic missile base drag continues to defy even well-rounded CFD codes. In an effort to address the accuracy and predictability of the base drags, the influence of grid system and competitive turbulence models on the base drag is analyzed. Characteristics of some turbulence models is reviewed through incompressible turbulent flow over a flat plate, and performance for the base drag prediction of several turbulence models such as Baldwin-Lomax(B-L), Spalart-Allmaras(S-A), $\kappa-\epsilon$, $\kappa-\omega$ model is assessed. When compressibility correction is injected into the S-A model, prediction accuracy of the base drag is enhanced. The NSWC wind tunnel test data are utilized for comparison of CFD and semi-empirical codes on the accuracy of base drag predictability: they are about equal, but CFD tends to perform better. It is also found that, as angle of attack of a missile with control (ins increases, even the best CFD analysis tool we have lacks the accuracy needed for the base drag prediction.