• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.505-505
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• 2012

플라즈마 제트에서 발생하는 전기적 충격을 제거하기위한 특성을 조사하였다. 바이오 플라즈마 연구에 사용되는 대기압 플라즈마 제트는 일반적으로 아르곤 등의 불활성 가스를 주입하고 고전압을 전극에 인가하여 플라즈마를 발생하는 방식이다. 저주파(수십~수백 kHz) 전원 장치로 발생하는 일반적인 플라즈마 제트에서의 전기적 데미지는 전류 값이 2 mA 이상일 때 발생한다. 본 실험에 사용한 장치는 석영관의 양단 끝에서 가스를 주입하여 석영관 중앙에 위치한 홀로 가스가 빠져나가는 구조이다. 석영관 양단 끝에 위치한 전극에 서로 반대 위상의 교류전원을 인가하고, 그로 인해 발생된 플라즈마는 중앙에 위치한 홀로 방출된다. 따라서 홀이 위치한 석영관 중앙의 전압은 수십 V로 측정되었으며, 이로 인한 전기적 충격이 없었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.196-199
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• 2011

Subscale high-pressure injection system which use two-stage light gas gun composed with high-pressure tube, pump tube and launch tube can make supersonic liquid jet. The supersonic liquid jet enhances droplet atomization by shockwave in front of the jet. In this study, the experiments was executed to identify the atomization characteristics of the supersonic liquid jet using straight cone nozzle. SMD which presents the atomization characteristics was decreased from $151.2{\mu}m$ to $52.25{\mu}m$ by increasing of L/d.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.97-106
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• 2018

This paper summarizes the technical difficulties pertaining the double-compression ramp scramjet inlet model testing in a shock tunnel and their corresponding solutions. Four technical difficulties are identified: 1) test facility unstart, 2) flow disturbance and model damage due to the impact of diaphragm debris, 3) lack of fuel jet development due to multiple injection, and 4) short test time. After overcoming the identified technical difficulties, the improved results were confirmed through the results of shadowgraph images and shock tube end wall pressure.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.11
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• pp.747-754
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• 2022

An experimental study was carried out to control a shock-induced boundary layer separation by utilizing the supersonic sweeping jet from the fluidic oscillator. High-speed schlieren, surface flow visualization, wall pressure measurement and precise Pitot tube measurement were applied to observe the influences of the location and the supply pressure of the fluidic oscillator on the characteristics of the oblique-shock-induced boundary layer separation. The characteristics of the separation control by the present supersonic fluidic oscillator was quantitatively analyzed by comparing with a conventional control method utilizing an air-jet vortex generator.

• Proceedings of the KSME Conference
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• 2003.04a
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• pp.2066-2070
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• 2003

This experimental study describes the propagation characteristics and suppression of the impulse noise emitted from the exit of a perforated pipe attached to the open end of a simple shock tube. The experiment is performed through the systematic change of the shock wave Mach number and the geometrical parameters such as the porosity, hole diameter and length of the perforated pipe. The experimental results for the near and far sound field are presented and explained in comparison with those for a straight pipe. The results obtained show that for the near sound field the impulse noise strongly propagates toward to the pipe axis, but for the far sound field the impulse noise uniformly propagates toward to the all directions, indicating that the directivity pattern is almost same regardless of the pipe type. Moreover, the noise reduction performance of perforated pipe depends upon the condition of sound field. For the near sound field the perforated pipe has a little performance to suppress the impulse noise, but for the far sound field the perforated pipe has little performance to suppress the impulse noise.

• Journal of the Korean Chemical Society
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• v.48 no.1
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• pp.12-16
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• 2004

The ignition of ethanol-oxygen-argon mixture was studied in reflected shock waves over the temperature range of 1281-1625 K and the pressure range of 0.69-1.06 bar. The ignition delay time was measured by the sudden increase of pressure profile and the radiation emitted by OH radicals. The relationship between the ignition delay time and the concentrations of ethanol and oxygen was determined in the form of mass-action expressions with an Arrhenius temperature dependence. In contrast to the behavior observed in methanol, ethanol acts to inhibit rather than accelerate its own ignition. Several kinetic mechanisms proposed for ethanol oxidation at high temperatures have been tested by the computer simulation.

• Fire Science and Engineering
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• v.5 no.3
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• pp.5-14
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• 1991

Now a days, according that the occurrence of industrial disaster is on the increase, the necessity of protective goods is increasing. Specially estimate of safety helmet for protect of head is very important. On this, in this paper, amplification ratio and natural frequencies of fire safety helmet and general safety helmet are estimated by falling impect test and frequency analysis. Also. trend of damping is estimated by using these test results. And we know that the fire safety helmet is more safe than general safety helmet for protect of head.

• Journal of the Korean Geotechnical Society
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• v.18 no.4
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• pp.271-283
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• 2002

P-wave velocity of concrete is a crucial parameter in determining the thickness of concrete lining, the location of cracks or other defects in Impact-Echo(IE) method. This study introduces an IE-SASW method that may determine the P-wave velocity on a surface of each testing area using the Spectral Analysis of Surface Wave (SASW) method. In numerical studies(Part I), it was verified that P-wave velocities could be obtained from SASW. In this paper(Part II), experimental studies were made in slab type concrete model specimens in which voids and waterproof sheet were included at the known locations. Accordingly, the feasibility of the proposed method was evaluated. The IE-SASW method was also performed in the precast model tunnel on ground and open-cut tunnel in ground. SASW tests were performed to determine the P-wave velocity of the concrete and then IE tests were carried at regularly spaced points along the testing lines to determine the thickness of structures. The nondestructive testing method which combined SASW and IE tests showed the great potential in the field applications.

• Journal of the Korean Society of Combustion
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• v.4 no.1
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• pp.59-65
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• 1999

Ignition of $NH_3-O_2-Ar$ mixtures have been studied behind reflected shock waves over the temperature range of 1600-2300 K and the pressures in the range of 1.1-1.6 atm. The pressure profile and the radiation emitted behind the shock waves have been monitored to give empirical correlations between ignition delay times and the mixture concentrations with the experimental conditions. On the basis of this data, several kinetic mechanisms proposed for ammonia oxidation at high temperatures have been tested. The ignition delay times obtained from the mechanism proposed by Miller and Smook were in good agreement with our experimental results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.98-101
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• 2003

The purpose of this research is to investigate the hypersonic reactive flow around hyperbolic shaped ballistic launcher, A numerical study was carried out to compare with the experimental results of hyperbolic shaped model, which were tested in a free piston shock tunnel, T3 in ANU. Freestream condition was 98% $N_2$, 2% $O_2$, and total enthalpy was 8MJ/kg. Also this paper used 2-temperature and 1-temperature model to show the difference of them.