• 한국연소학회:학술대회논문집
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• 한국연소학회 2014년도 제49회 KOSCO SYMPOSIUM 초록집
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• pp.87-89
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• 2014

Spherically expanding flames are used to measure flame speeds, which are derived the corresponding laminar flame speeds at zero stretch. Flame speeds of n-butanol at high pressure are studied over an extensive range of equivalence ratios. The classical shadowgraph technique is used to detect the reaction zone. In analytical methodology the optimization process using least mean squares is performed to extract the laminar flame speeds. Laminar flame speeds are compared with results obtained from numerical work.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2013년도 제46회 KOSCO SYMPOSIUM 초록집
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• pp.103-105
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• 2013

Spherically expanding flames are used to measure flame speeds, which are derived the corresponding laminar flame speeds at zero stretch. Dimethyl Ether-Air mixtures at high pressure are studied over an extensive range of equivalence ratios. The classical shadowgraph technique is used to detect the reaction zone. In analytical methodology the optimization process using least mean squares is performed to extract the laminar flame speeds. Laminar flame speeds are compared with results reported in the literature.

• 한국연소학회지
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• 제19권1호
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• pp.11-16
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• 2014

Spherically expanding flames are used to measure flame speeds, which are derived the corresponding laminar flame speeds at zero stretch. Dimethyl Ether-Air mixtures at high pressure are studied over an extensive range of equivalence ratios. The classical shadowgraph technique is used to detect the reaction zone. In analytical methodology the optimization process using least mean squares is performed to extract the laminar flame speeds. It is seen that the laminar flame speed of DME-Air mixture with the increase of pressure decreases rapidly showing a similar trend to other hydrocarbon fuels. At pressure of 2 and 10 atm the experimental data from the present study agree well with results reported in the literature. Especially the laminar flame speeds at 2 atm are in good agreement with those calculated in numerical work over the full stoichiometric range. At elevated pressure of 12 atm the measured data are slightly slower at fuel lean condition and show close agreement at fuel rich condition when compared with the numerical results.

• 한국항공우주학회지
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• 제45권8호
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• pp.619-626
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• 2017

마하수 6 조건에서 반구 모델에 대해 자세각의 변화에 따른 항력계수를 연구하였다. 충격파 터널에서 실험이 진행되었으며 지지대 유동 간섭을 최소화하기 위해 자유낙하 기법을 사용하였다. 자유낙하하는 반구 모델의 자세와 항력계수를 측정하기 위해 계단식 모듈과 전자석을 이용한 자유낙하 기법을 구축하였고 초고속 카메라를 통한 shadowgraph 기법을 사용하였다.

• 한국가시화정보학회지
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• 제11권2호
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• pp.46-54
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• 2013

Study of the wave structure and shear layer in the vicinity of a wall mounted cavity is done by time averaged colour schlieren and time resolved instantaneous shadowgraph technique in an M=1.7 flowfield. Effect of change of cavity width on flow structure is investigated by using constant length to depth (L/D) ratio cavity models with varying length to width (L/W) ratio of 0.83 to 4. The time averaged shock wave structure was observed to change with change in cavity width. Dependence of the shock angle at the leading edge on the shear layer width is also evident from the images obtained. Unsteadiness in the flow field in terms of shear layer dynamics and quasi steady nature of shock waves was evident from the images obtained during instantaneous shadowgraph experiments. Apart from the leading and trailing edge shocks, several other waves and flow features were observed. These flow features and the associated physical phenomena are discussed in details and presented in the paper.

• 한국항공우주학회지
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• 제44권2호
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• pp.99-107
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• 2016

본 연구에서는 Infra-Red Thermography(IRT) 기법을 활용한 초음속 풍동시험 시 의도치 않게 발생하는 기술적 문제에 대한 연구를 수행하였으며 이를 방지할 수 있는 방법에 대해 분석하였다. 풍동시험은 마하 3 또는 4의 두 가지 유동조건에서 초고속 비행체 형상을 모사할 수 있는 이중 압축램프 모델로 수행하였다. 획득된 IR 결과를 shadowgraph 가시화 이미지, 수치해석 결과와 비교하였으며 본 IRT 기법을 활용하여 초음속 이중 압축램프에서 발생하는 유동천이, 박리 그리고 3차원 현상에 관한 정성적인 정보를 획득할 수 있음을 확인하였다.

• International Journal of Aeronautical and Space Sciences
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• 제18권1호
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• pp.38-47
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• 2017

This paper presents experimental data on water droplet breakup in high-speed air flows. Exact-time-dependent evolution of wave and droplet interaction as well as breakup processes were optically visualized using a shadowgraph technique. Droplet experiments were conducted in a shock tube. Five flow conditions were used with an incident shock wave Mach number from 1.40 to 2.19 with Weber number based on the droplet initial diameter from 2300 to 38000, respectively. This corresponds to post-shock flow speeds varying from subsonic to supersonic. The considered droplet diameters were 2.0 mm to 3.6 mm. Some interesting wave patterns in the near wake were found. The present data shows that with an increase in the Weber number the droplet acceleration coefficient decreases and the level of decrease was weaker for the case of higher Mach numbers. This state of affair is different to the existing data in literature. Possible reasons are discussed.

• 한국항공우주학회지
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• 제50권5호
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• pp.333-338
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• 2022

쉐도우그래프(Shadowgraph) 기법을 통해 케로신의 대체 물질인 데칸/메틸사이클로헥산 혼합연료를 사용하는 단일 제트(jet)를 초임계 환경으로 분사하여 제트의 거동을 가시화하였다. T_r = 0.484인 연료 제트의 분사 차압 ∆P는 0.5 MPa로 일정하게 유지하였고 혼합연료의 임계점 이상에서 실험을 진행하였으며 챔버 내부 환산온도 T_r(=T/T_c)를 1.00~1.23, 환산압력 P_r(=P/P_c)을 1.00, 1.38로 변화하여 실험결과를 분석하였다. 초임계 환경으로 분사되는 제트의 밀도감소 지표로써 후처리 된 제트 이미지의 밝기 강도를 챔버 내부 온도와 압력을 변화시켜 관찰하였다. 챔버 내부 온도가 상승할 때 제트의 밝기 강도 감소 폭이 커지는 것을 확인하였으며, 동일 온도일 때 챔버 내부 압력이 높을 경우 제트의 밝기 강도 감소가 지연되는 것을 확인하였다. 챔버 내부 압력이 높을 경우 연료의 유사 임계온도(pseudocritical temperature)가 증가하고 연료 제트의 밀도감소에 필요한 온도가 상승하여 밝기 강도 변화가 지연되는 근거로 판단하였다.

• 한국분무공학회지
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• 제11권2호
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• pp.105-112
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• 2006

A unique feature of fluidic atomizers is that the nozzle geometry produces a thin capillary Jet which is forced to oscillate on a 2-dimensional plane through the use of a passive feedback mechanism. The objective of the current work is to characterize the influence of the stagnation pressure at the nozzle exit, jet oscillation and stretching on the breakup properties of the capillary ligament. To achieve this, shadow graph technique is used to measure size, shape, velocity and the number density of the droplets as a function of the position within the spray fan. The breakup length, defined as the radial distance from the breakup point, is analyzed as a function of the non-dimensional parameters. Finally, a kinematic model is developed to simulate the breakup of the oscillating jets at low stagnation pressures. Using the existing jet breakup theories, the model is used to predict the size and diameter distribution of the droplets after primary atomization.

• 대한기계학회논문집B
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• 제30권7호
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• pp.682-691
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• 2006

This study was conducted to assess the effect of mixed fuel composition and mass fraction on spray inner structure in evaporating transient spray under the various ambient conditions. Spray structure and spatial distribution of liquid phase concentration are investigated using a thin laser sheet illumination technique on the multi-component mixed fuels. A pulsed Ar+ laser was used as a light source. The experiments were conducted in a constant volume vessel with optical access. Fuel was injected into the vessel with electronically controlled common rail injector. Used fuel contain $i-octane(C_8H_{18}),\;n-dodecane(C_{12}H_{26})$ and $n-hexadecane(C_{16}H_{34})$ that are selected as low-, middle- and high-boiling point fuel, respectively. Experimental conditions are 25Mpa, 42MPa, 72MPa and 112MPa in injection pressure, $5kg/m^3,\;15kg/m^3\;and\;20kg/m^3$ in ambient gas density, 400K, 500K, 600K and 700K in ambient gas temperature, 300K and 368K in fuel temperature, and different fuel mass fraction. Experimental results indicate that the more high-boiling point component, the longer the liquid phase it were closely related to fuel physical properties, but injection pressure had no effect on. And there was a high correlation between the liquid phase length and boiling temperature at 75% distillation point.