• 한국추진공학회지
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• 제5권2호
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• pp.73-82
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• 2001

제트엔진을 중심으로 유도탄용 아음속 공기흡입식 추진기관의 실례를 분석하고, 그 개발에 소요되는 기술의 현황과 전망을 기술하였다. 여기에 서술한 내용은 동종의 유도탄 뿐만 아니라, 무인항공기나 소형 항공기의 추진기관에 대한 기술적 이해에 도움이 될 것이다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2001년도 추계 학술대회논문집
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• pp.138-143
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• 2001

An experimental model to enhance the mixing of parallel supersonic-subsonic jet ($M_1$=1.78 and $M_2$=0.30) is simulated with a numerical technique by modeling the wall-mounted cavity to a boundary condition of oscillating pressure. The computed pilot pressure distributions along three representative cross sections show a good agreement with the equivalent experimental data. The irradiation of acoustic wave in the ultrasonic range causes the mixing augmentation of jet and wake due to the transfer of vibration energy between fluid particles.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2002년도 제24회 KOSCO SYMPOSIUM 논문집
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• pp.147-153
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• 2002

Experimental investigations are performed on the stability and the structure of bluff-body stabilized hydrogen flames. The velocities of coflow air are varied from subsonic to supersonic velocity of Mach 1.8 and OH PLIF images and Schilieren images are used for analysis. Three characteristic flame modes are classified into three regimes with the variation of fuel-air velocity ratio; a jet like flame, a central-jet dominated flame and a recirculation zone flame. Stability curves are drawn to find the blowout regimes and to show that flame stability is improved by increasing the lip thickness of fuel nozzle that works as bluff-body. $Damk{\ddot{o}hler$ number is adopted in order to scale the blowout curves of each flame obtained at different sizes of the bluff-body and all blowout curves are scaled successfully regardless of its bluff-body size.

• 항공우주기술
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• 제8권1호
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• pp.154-161
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• 2009

자연적으로 빠르게 성장하는 불안정성 파동을 자극하기위한 순수하고 제어 가능한 자극 파동을 생성하기는 쉽지 않다. 이를 위하여 순/역방향 스월제트를 발생시킬 수 있는 장치가 설계, 제작, 응용되었으며, 기계적 자극을 유도할 수 있는 독특한 장치가 고안되었다.

• Journal of Mechanical Science and Technology
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• 제15권10호
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• pp.1423-1433
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• 2001

A flow modeling method has been developed to analyze the flow in the annular base (rear- facing surface) of a circular engine nacelle flying at subsonic speed but with a supersonic exhaust jet. Real values of exhaust gas properties and temperature at an altitude of 30, 000 feet are employed. 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. Conserva- tion of mass, momentum and energy for the wake flow field is achieved by multiple iterations with modest computer requirements.

• 한국추진공학회지
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• 제12권6호
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• pp.38-47
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• 2008

횡방향으로 유입되는 공기유동에서 연료 제트의 액주 및 액적영역의 궤적에 관한 연구를 수행하였다. 실험방법으로는 직접사진촬영방법과 평면레이저유도형광 기법을 사용하여 분석하였다. 본 연구의 목적은 공기유동 방향에 수직으로 분사되는 분무와 분사각도의 분무에서 궤적에 대한 경험식을 도출하여 기존 연구결과와 비교분석하고, 대향분사에서의 궤적에 대한 경험식을 도출하는데 있다. 실험을 통하여 액주 및 액적 영역의 궤적은 연료분사차압, 공기의 유속, 분사기 지름 크기, 분사각도에 의하여 결정되며, 정방향의 분무와 대향분사 결과에 있어서는 실험식 상수의 차이가 있음을 확인하였다.

• 대한기계학회논문집B
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• 제33권9호
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• pp.666-673
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• 2009

The turbulent swirling flow field characteristics of a gun-type gas burner with a combustion chamber were investigated under the cold flow condition. The velocities and turbulent quantities were measured by hot-wire anemometer system with an X-type probe. The turbulent swirling flow field in the edge of a jet seems to cause a recirculation flow from downstream to upstream due to the unbalance of static pressure between a main jet flow and a chamber wall. Moreover, because the recirculation flow seems to expand the main jet flow to the radial and to shorten it to the axial, the turbulent swirling flow field with a chamber increases a radial momentum but decreases an axial as compared with the case without a chamber from the range of about X/R=1.5. As a result, these phenomena can be seen through all mean velocities, turbulent kinetic energy and turbulent shear stresses. All physical quantities obtained around the slits, however, show the similar magnitude and profiles as the case without a chamber within the range of about X/R=1.0.

• Advances in aircraft and spacecraft science
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• 제6권6호
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• pp.515-528
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• 2019

The structural vibrations of a flat plate induced by fluctuating wall pressures within wall-bounded transonic jet flow downstream of a high-aspect ratio rectangular nozzle are simulated. The wall pressures are calculated using Hybrid RANS/LES CFD, where LES models the large-scale turbulence in the shear layers downstream of the nozzle. The structural vibrations are computed using modes from a finite element model and a time-domain forced response calculation methodology. At low flow speeds, the convecting turbulence in the shear layers loads the plate in a manner similar to that of turbulent boundary layer flow. However, at high nozzle pressure ratio discharge conditions the flow over the panel becomes transonic, and the shear layer turbulence scatters from shock cells just downstream of the nozzle, generating backward traveling low frequency surface pressure loads that also drive the plate. The structural mode shapes and subsonic and transonic surface pressure fields are transformed to wavenumber space to better understand the nature of the loading distributions and individual modal responses. Modes with wavenumber distributions which align well with those of the pressure field respond strongly. Negative wavenumber loading components are clearly visible in the transforms of the supersonic flow wall pressures near the nozzle, indicating backward propagating pressure fields. In those cases the modal joint acceptances include significant contributions from negative wavenumber terms.

• 한국분무공학회지
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• 제7권3호
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• pp.12-17
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• 2002

In this paper, spray and combustion characteristics of a liquid-fueled ramjet engine were experimentally investigated. The spray penetrations were measured to clarify the spray characteristics of a liguid jet injected transversely into the subsonic vitiated airstream, which is maintained a high velocity and temperature. The spray penetrations are increased with decreasing airstream velocity, increasing airstream temperature, and increasing air-fuel momentum ratio. To compensate our results of penetrations, the new experimental equation were modified from Inamura's equation. In the case of insufficient penetration, the combustion phenomenon in ram-combustor were unstable. Therefore, the temperature distribution was slanted to the low wall of the ram-combustor. These trends gradually disappeared as the length and air temperature of the combustor became longer. Combustion efficiency increased when the length of the combustor was long and the air temperature was high. Especially, stable flame region is enlarged when the length of the combustor was long and the air temperature was high. Type Abstract here. Type Abstract here.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.320-324
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• 2017

아음속 공기유동으로 수직분사하는 액체제트에 대하여 오리피스 형상이 달라질 경우, 분무특성에 어떠한 영향을 미치는지 실험적으로 연구하였다. 서로 다른 오리피스 길이 대 직경비와 타원형 노즐의 종횡비를 갖는 분사기들을 제작하여 수직분사 실험을 진행하였다. 원형노즐과 타원형 노즐에서의 분열길이를 비교하였으며, 타원형 노즐에서의 분열길이는 모든 실험조건에서 원형노즐에 비해 줄어들었다. 캐비테이션과 수력튀김 현상이 분사기 내부에 발달되는 분무차압 조건의 경우, 두 노즐 모두 분열길이가 감소하였다. 액주궤적의 경우, 장축으로부터 분무되는 액체제트가 횡방향 공기유동에 수직으로 부딪혀 나가는 경우가 액주의 궤적이 단축에 비해 더 휘어지며, 침투높이가 낮아진다.