• Journal of computational fluids engineering
• /
• v.8 no.4
• /
• pp.58-61
• /
• 2003

• Journal of the KSME
• /
• v.46 no.4 s.305
• /
• pp.45-50
• /
• 2006

• Journal of the Korean Society of Visualization
• /
• v.20 no.3
• /
• pp.1-9
• /
• 2022

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.12
• /
• pp.1059-1066
• /
• 2007

An experimental study has been conducted to investigate the flow separation control effects of a blowing jet on an elliptic airfoil at a Reynolds number of 7.84×105 based on the chord length. A blowing jet was obtained by pressing a plenum inside the airfoil and ejecting flow out of a thin jet slot that located in leading edge or trailing edge. The experimental results have shown that the blowing jet had an effect of suppressing the flow separation, resulting in the higher suction pressure distribution and higher normal force. The increase in Cn was more pronounced at higher incidence, whereas the effectiveness of the blowing jet reduced at lower incidences. The leading edge pulsating blowing with 90° was the most effective in controlling the flow separation than other types of blowing jet configuration tested in this research. Moreover, when the pulsating blowing was applied, the stall angle was postponed about 2°-3°. The continuous and pulsating blowing jet is a direct and effective flow separation control for improving the aerodynamic characteristics and performances of airfoil.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.32 no.5
• /
• pp.10-17
• /
• 2004

To achieve the advanced forward flight performance of helicopter, the passive control methods for enhancement of the dynamic stall characteristics of rotor blades are studied. To enhance the dynamic stall characteristics of the rotor blades, it is essential to improve the lift performance and the pitching moment performance simultaneously with the control of the separation on the rotor blades. For this point of view, both the fixed droop leading edge and the Gurney flap which are simply realized are used for control of the dynamic stall in severe dynamic stall conditions. From this study, the combination of both passive control methods showed dramatic enhancement of lift and pitching moment performance in dynamic stall than previous research results.

• Proceedings of the Korean Information Science Society Conference
• /
• 2003.10a
• /
• pp.637-639
• /
• 2003

컴퓨터 시스템의 발달로 인해 여러 사용자가 여러 자원을 동시에 사용할 수 있는 환경으로 발전하면서 기존의 사용자 기반의 접근제어가 아닌 역할을 중심으로 하는 접근제어 모델이 제안되었다. 이러한 역할기반 접근제어 기법을 위한 참고 모델로서 역할 그래프 모델이 소개되었지만, 엄격한 충돌 처리 방식 때문에 실제 응용시스템에 적용하는 것은 한계가 있었다. 본 논문에서는 이러한 한계를 극복하기 위해서 충돌되는 권한을 세분화하고 이를 이용하여 좀 더 유연한 권한 삽입 연산을 할 수 있도록 하였다. 이러한 유동적 권한 삽입 방식을 통해 역할 그래프 모델을 좀 더 다양하게 적용한 수 있을 것이다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1999.10a
• /
• pp.34-34
• /
• 1999

일반적으로 배관계를 통하는 유체 유량을 조절하거나 감압하는 목적으로 각종 밸브가 널리 이용되고 있다. 이러한 밸브는 작동 유체의 종류나 밸브형상에 따라 여러 가지로 분류할 수 있으나, 밸브가 유동에 미치는 저항특성, 밸브에서 발생하는 유동관련 소음진동, 기밀도, 내구 및 보수성 등을 고려하여 적절한 밸브를 선정하게 된다. 종래 버터플라이 밸브는 주로 비압축성 유체유동을 조절하기 위하여 사용되어 왔으나, 최근 다양한 방면에서 압축성 유동을 제어하기 위하여 그 활용이 증대되고 있다. 이것은 버터플라이 밸브의 형상이 매우 단순하여 밸브가 유동에 미치는 저항이 작으며, 제작 및 설치가 용이하기 때문이다.

• Bulletin of the Society of Naval Architects of Korea
• /
• v.32 no.1
• /
• pp.21-27
• /
• 1995

초고속선에 관련된 점성유동은 저한성능 향상과 운항자세 제어를 위해 사용되는 다양한 선체부 가물의 저항 예측과 초고속선에 많이 사용되는 물분사 추진장치 입구 형상의 설계 그리고 임펠 러에 이르는 덕트 유동의 예측을 중심으로 관심을 받아왔다. 본 소고에서는 통상적인 선박의 경우와는 구별되는 초고속선 고유의 점성유동 특성에 관하여 간략히 논의하기로 하고 내용을 크게 선체-부가물 점성유동과 물분사 추진장치에 관련되어 있는 덕트유동으로 나누어 기술하 였다.

• Journal of Advanced Marine Engineering and Technology
• /
• v.33 no.8
• /
• pp.1180-1186
• /
• 2009

This experimental study is about the flow characteristics according to existence and nonexistence of the control rod and location in the flow field where it has the Inclined rear walls in the open cavity. By using the visualization of flow and particle image velocimetry (PIV), we performed about a change and speed of the Reynolds number. Our objective was what part of the control rod gives less effects to the characteristics of flow and how the shear mixing layer moves at what critical point of the Reynolds number. As a result, we differed the location of control rod. So finally, L/H=0.2 was discovered to give less effects to the cavity. The flow of backside of vortex faces the upper side. And we found that this phenomenon shows up more clear when the number of Reynolds increases. This is because of the flow of vortex causes by the condition of y/H=1.0. This phenomenon gets more clear with increasing of number of Reynolds, and critical point of the Reynolds number was $Re=1.0{\times}10^4$ around. If control rod is L/H=0.1, depending on the number of Reynolds ($Re=6.0{\times}10^3$, $Re=8.0{\times}10^3$, $Re=1.0{\times}10^4$, $Re=1.2{\times}10^4$), doubled vortex shows up. As the shear mixing layer of the upper side of cavity increases, the speed of the lower side was very stable.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.4 no.1
• /
• pp.13-21
• /
• 2000

The advantages of the SITVC (Secondary Injection for Thrust Vector Control) technique over mechanical thrust vectoring systems include a reduction in both the nozzle weight and complexity due to the elimination of the mechanical actuators that are used in conventional vectoring. The optimal operating conditions of SITVC were investigated using in-house developed compressible flow analysis codes. Numerical experiments were used to examine the impact of the thrust vector direction with a variety of injection positions, mass flow rates, and injection angles on the two-dimensional expansion cone of a supersonic nozzle. The computational results showed that the optimal position of the secondary injection, with the maximum deviation angle and side thrust, was where the oblique shock generated by the secondary injection reached the end of the nozzle exit.