• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.703-712
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• 2004

A variant of the magnetoplasma jet engine (magjet) is here proposed for airbreathing flight in the hypersonic regime. As shown in Figure 1, the engine consists of two distinct ducts: the high-speed duct, in which power is added electromagnetically to the incoming air by a momentum addition device, and the fuel cell duct in which the flow stagnation temperature is reduced by extracting energy through the use of a magnetoplas-madynamic (MPD) generator. The power generated is then used to accelerate the flow exiting the fuel cells with a fraction bypassed to the high-speed duct. The analysis is performed using a quasi one-dimensional model neglecting the Hall and ion slip effects, and fix-ing the fuel cell efficiency to 0.6. Results obtained show that the specific impulse of the magjet is at least equal to and up to 3 times the one of a turbojet, ram-jet, or scramjet in their respective flight Mach number range. Should the air stagnation temperature in the fuel cell compartment not exceed 5 times the incoming air static temperature, the maximal flight Mach number possible would vary between 6.5 and 15 for a magnitude of the ratio between the Joule heating and the work interaction in the MPD generator varied between 0.25 and 0.01, respectively. Increasing the mass flow rate ratio between the high speed and fuel cell ducts from 0.2 to 20 increases the engine efficiency by as much as 3 times in the lower supersonic range, while resulting in a less than 10% increase for a flight Mach number exceeding 8.

• 한국수자원학회논문집
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• 제32권2호
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• pp.153-162
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• 1999

본 연구에서는 정지수체에서 다공확산관을 통해 방류된 연직다중의 혼합 및 희석 특성에 대해 규명하였다. 3차원 실험수조에서 실험을 통해 밝혀진 결과는 다음과 같다. 우선 다공확산관의 병합과정을 살펴보면 흐름의 안정조건에 따라 병합거리가 다소 차이가 있기는 하지만 {{{{ { z}_{ } }}}}/{{{{ {l}_{ } }}}}가 대략 3인 지점부터 병합이 시작되어 그 이후에는 평면부력？의 거동에 서서히 가까워짐을 알 수 있다. 최소희석률에 대해 분석해 본 결과, 방류운동량이 지배적인 영역, 천이영역, 그리고 부력이 지배적인 부력류영역으로 나누어 희석률 특성을 표현할 수 있음을 알 수 있었다. 본 연구의 실험결과 다공확산관의 경우 부력류영역의 희석률 상수가 평면확산관에 비해 15% 더 높게 나왔다. 그 이유는 다공확산관의 경우 병합 이전에는 개별의 경계면에서 주변수의 포획이 발생하여 희석이 증대되기 때문이다.

• 한국항해항만학회지
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• 제37권3호
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• pp.257-262
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• 2013

거친 바다를 운항하는 선박의 경우 횡 동요로 인해 선박 내의 장비운영 문제 및 탑승객들에게 큰 불편함을 초래한다. 따라서 횡동요 감쇠를 위한 목적으로 빌지 킬, 핀 안정기, 자이로스코프, ART(Anti-Rolling Tank), 타, 플랩 등 다양한 횡 동요 감쇠장치들이 사용되고 있다. 콴다효과는 콴다제트가 곡면의 표면을 따라 흐르며 주위 유동의 순환을 증가시켜 양력을 효과적으로 발생시키는 방법으로 핀의 양력성능을 향상시킬 수 있다. 본 연구에서는 모형시험 및 수치계산을 통해 콴다효과를 적용한 고정식 핀 안정기의 사용가능성을 검토하였다. 그 결과 받음각이 $0^{\circ}$에서, 제트모멘텀을 $C_j$ = 0.25 만큼 공급할 때, 기준 핀의 최대 작동각($26^{\circ}$)에서 발생되는 양력과 동일하게 발생되는 것으로 나타났다. 즉 받음각을 변화시키는 기존의 핀 안정기와 달리 받음각을 고정하고, 콴다효과를 통한 제트유동제어만으로 선박의 횡 동요를 능동적으로 제어 할 수 있을 것으로 보인다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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• pp.229-234
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• 2006

The oxy-fuel combustion heating characteristics is investigated experimentally by measuring furnace and steel temperature variations for batch type furnace simulator with a specially designed low NOx oxy-fuel burner. Economics of using oxy-fuel combustion is confirmed and, the furnace and steel temperature variations for different heating conditions are compared to deduce optimal heating control pattern for energy savings and rapid uniform heating. High $CO_2$ concentration (> 80-90%), low NOx (< 40ppm) and CO (< 10ppm) are measured in the flue gas. Temperature differences (< $30^{circ}C$) inside the furnace and steel are reduced relatively by increasing the burner jet momentum.

• 한국해양공학회지
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• 제30권1호
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• pp.18-24
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• 2016

Stabilizer fins are installed on each side of a ship to control its roll motion. The most common stabilizer fin is a rolling control system that uses the lift force on the fin surface. If the angle of attack of a stabilizer fin is zero or the speed is zero, it cannot control the roll motion. The Coanda effect is well known to generate lift force in marine field. The performance of stabilizer fin that applies the Coanda effect has been verified by model tests and numerical simulations. It was found that a stabilizer fin that applied the Coanda effect at Cj = 0.085 and a zero angle of attack exactly coincided with that of the original fin at α = 26°. In addition, the power needed to generate the Coanda effect was not high compared to the motor power of the original stabilizer fin.

• 한국추진공학회지
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• 제3권2호
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• pp.66-74
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• 1999

본 연구에서는 송풍기의 출력이 일정한 상태에서 열전달 계수의 증가를 가져오기 위한 방법으로 다공판을 이용하였다. 이 방법은 다공판에 의한 운동량 감소 등의 몇 가지 단점이 있지만 특정한 조건에서 사용될 때, 정체 유동 영역에서 다공판이 없는 경우보다 최고 2배 이상 열전달 계수가 증가하였다. 본 연구에서는 정확하고 간편한 실험을 위하여 액정을 온도 지시계로 사용하였으며, 액정을 이용하면 열전대 등을 온도 지시계로 이용하는 실험보다 훨씬 간단하고 정확한 실험이 가능하다는 것을 알 수 있었다.

• 한국전산유체공학회지
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• 제6권2호
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• pp.1-8
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• 2001

Despite the massive effort which has been given to the analysis of the base flows, one commonly occurring case seems to be overlooked. This is for base (rearward facing surface) which is between a subsonic flow and supersonic flow. Potential flows of the air and gas streams are computed for the flow past a separated wake. Then a viscous jet mixing is superimposed on this inviscid solution. Conservation of mass, momentum and energy is achieved by multiple iterations. Despite the iterations, the wake flow field is computed with modest computer requirements.

• 천문학회지
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• 제29권spc1호
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• pp.201-204
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• 1996

Magnetic fields are thought to playa role in a wide variety of important astrophysical processes, from angular momentum transport and jet formation in accretion disks to corona formation in stars. Unfortunately, the dynamics of magnetic fields in astrophysical plasmas are extremely complicated, and the success of current theoretical models and computer simulations seems to be inversely correlated with the amount of observational detail available to us. Here I will discuss some of the more striking conflicts between numerical simulations and observations, and present an explanation for them based on an important dynamical process which is not adequately modeled in current numerical simulations. These processes will lead to the formation of flux tubes in stars and accretion disks, in accordance with observations. I will discuss some of the implications of flux tube formation for stellar and accretion disk dynamos.

• 대한기계학회논문집B
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• 제29권2호
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• pp.205-213
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• 2005

The drop ejection process from a micro nozzle is investigated by numerically solving the conservation equations for mass and momentum. The liquid-gas interface is tracked by a level set method which is extended for two-fluid flows with irregular solid boundaries. Based on the numerical results, the liquid jet breaking and droplet formation behavior is found to depend strongly on the pulse type of forcing pressure and the contact angle at the gas-liquid-solid interline. The negative pressure forcing can be used to control the formation of satellite droplets. Also, various nozzle shapes are tested to investigate their effect on droplet formation.

• Journal of Mechanical Science and Technology
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• 제15권2호
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• pp.259-267
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• 2001

The flow field in a cylinder of a 4-valve pentroof engine is studied using the KIVA-3V code. Turbulence is generated from the jet flow through valves and broken down to the small scale eddies in the compression process. It is known that the tumble effectively keeps turbulence during the compression process. In the combustion process, turbulence is known to enhance flame speed by increasing mass, momentum and heat transfer rates. The effects of the intake port angles on the flow and combustion characteristics are studied in this study. To study the effect of turbulence on the combustion process, Cantore combustion model is applied in this study.