• Proceeding of EDISON Challenge
• /
• 2016.03a
• /
• pp.518-522
• /
• 2016

항공기 운항 중 사고가 가장 많이 발생하는 순간이 이착륙 순간이다. 사고의 원인은 실속(Stall)으로 인한 조종성 상실, 버드 스트라이크 등의 이유들이 있다. 본 연구에서는 항공기 날개에 구멍을 내서 구조적인 변화를 통해 이 착륙 시에 가장 많이 적용되는 받음각인 $10^{\circ}$에서 흐름의 박리가 지연되고, 양항비가 상승되는 효과를 기대하고 $10^{\circ}$이외의 받음각에서 박리가 지연되는지 해석을 진행하였다. 본 연구에서의 최종적 목표는 곡선형태의 구조변화 형상과 이를 실제 항공기에 적용이 가능하도록 제작성과 경제성을 고려하여 단순화 하는 작업을 진행하고 곡선 형태와 같은 효과를 얻고자 해석을 진행하였다. 받음각 $10^{\circ}$에서 해석을 진행한 경우 모든 형상들이 흐름의 박리를 지연시키는 효과를 가져왔다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.6
• /
• pp.10-17
• /
• 2006

NACA23012익형에 대하여 synthetic jet을 이용하여 박리 제어를 수행하였다. 공력특성의 향상을 위해 앞전 droop과 plain flap의 박리 부근에 synthetic jet을 위치시켰다. 고 받음각에서 앞전 박리의 발생으로 인한 실속을 앞전 droop의 작동과 이때 발생하는 앞전 박리를 synthetic jet으로 효과적으로 지연시킬 수 있고, 또한 실속 특성을 개선 할 수 있음을 확인하였다. 양력의 향상을 위하여 plain flap을 장착하였고, 이때 발생하는 박리를 synthetic jet으로 지연시켜 제어면의 작동 효율을 증가 시킬 수 있음을 확인하였다. 앞전 droop과 plain flap으로 구성된 간단한 고양력 장치에 발생하는 박리를 synthetic jet으로 제어함으로 실속을 지연시킴과 동시에 실속 특성을 향상시키고, 최대 양력의 증가로 fowler flap에 버금가는 공력특성을 확보할 수 있음을 확인하였다.

• Proceeding of EDISON Challenge
• /
• 2016.03a
• /
• pp.571-575
• /
• 2016

두꺼운 에어포일은 받음각이 클 때 역압력 구배가 일어날 수 있기 때문에 날개의 중앙부 후방에서 유동박리(Flow separation)와 와류 진동(Vortex shedding)이 쉽게 발생할 수 있다고 알려져 있다. 항공기가 이 착륙할 때 받음각이 커짐에 따라 유동박리에 의한 실속이 발생할 수 있는데 이를 지연 시켜 실속각을 크게 하면 안전성이나 효율 면에서 유리하다. 이를 위해 날개에 Hole을 만들어 와류를 잡아 유동의 박리를 지연시키고자 하였다. 본 연구에서는 EDISON_CFD 시스템의 2D_Incomp_P 솔버를 사용하여 NACA0018 에어포일의 윗면에 다른 위치의 Hole이 있을 때와 크기가 다른 Hole이 있을 때의 실속각이 가장 커지는 경우를 찾아보았다. Hole의 위치와 반지름 크기를 변화시켰을 때 각각의 최대 양력 계수를 비교하여 실속각의 증가와 Streamline을 그려 유동박리가 지연됨을 확인하였다.

• Composites Research
• /
• v.12 no.3
• /
• pp.1-7
• /
• 1999

New hybrid composite material CPAL(Carbon Patched ALuminum alloy), an Al2024-T3 plate doubleside reinforced with carbon/epoxy laminates were made. Fatigue crack growth tests were carried out at R=0.2, 0.5 in the CPAL specimens. The retardation mechanism and behavior of fatigue crack growth were examined basing on investigation of the crack and the delamination using a X-Ray and a ultrasonic C-Scan. The fatigue crack growth rates of CPAL specimens were remarkedly retarded compared to that of the Al2024-T3 specimen. The retardations amounts of the fatigue crack growth rates get higher in $0^{\circ}$/$90^{\circ}$ CPAL specimen than in $\pm$$45^{\circ}$ CPAL specimen, and get higher at R=0.2 than at R=0.5. The retardation of fatigue crack growth rates in CPAL specimen was generated by the crack bridging mechanism, that is the behavior that the fibers in CFRP layers decrease the COD in the Al2024-T3 plate.

• Journal of the Korean Wood Science and Technology
• /
• v.31 no.5
• /
• pp.35-42
• /
• 2003

This study was conducted to estimate peeling and vapor adsorption properties made with fabric glass fiber reinforced laminated timber according to our earlier report(Jung et al., 2002). In adsorption peeling test, three all types solid wood were not appeared the peeling. However, solid wood appeared to the peeling in boiling peeling test except for control wood. Vapor adsorption test was performed at 40℃, 90% relative humidity for 48 hours. Cross sections were not different all solid wood. Radial section and tangential section with glass fiber were delayed vapor adsorption compared to control wood. In anisotropy of vapor adsorption, solid wood with glass fiber were small values.

• Proceedings of the Korea Concrete Institute Conference
• /
• 2010.05a
• /
• pp.73-74
• /
• 2010

The objective of this research is to improve the flexural capacity of RC Beams. To delay prematured tension failure of concrete specimen and to improve flexural capacity of RC beam by increasing the contribution of FRP strengthening plates, a method for inserting a laminate to the interface between concrete and FRP materials. This method makes it possible to increase overall flexural performance of RC beam by FRP plate compared to normal RC beams and RC beam strengthened by bonded FRP plates. The new bonding technique is applicable to all types of reinforcement available FRP laminate, and in principle is also applicable to materials other than FRP.

• Proceedings of the Korean Nuclear Society Conference
• /
• 2003.10a
• /
• pp.81.1-81.1
• /
• 2003

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.46 no.1
• /
• pp.10-17
• /
• 2018

The size of commercial wind turbines has been increased. Generally, the pitch control is used to increase the efficiency of wind turbine. However, the pitch control has difficulty to control the local unsteady flow control which makes fatigue load and decreases the efficiency. In this research, Synthetic Jet Actuators(SJAs) are manufactured and applied into a wing section to delay flow separation and increase aerodynamic performances. The SJAs as a kind of zero-net mass-flux actuators injects and removes fluid through a small orifice with a given frequency. The SJA modules actuated by piezoelectric disks are manufactured and the aerodynamic performances are measured according to the shape of the orifice and the velocity of the jets through the wind tunnel test. It is confirmed that as the velocity of the jets are increased using rectangular shape orifice, drag force is decreased and lift force in increased.

• 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.34 no.8
• /
• pp.8-15
• /
• 2006

Separation control has been performed using the multi-array/multi-location synthetic jet on NACA23012 at high angle of attack. The flow control using single synthetic jet shows that stall characteristics can be substantially improved with delayed separation point. Theses results show the characteristic of unsteady flow of single synthetic jet. Beside, we researched on multi-array synthetic jet to obtain applicable synthetic jet velocity. Multi-location synthetic jet is proposed to eliminate small vortex on suction surface of airfoil. With the results, we concluded that the flow around airfoil is stable by high frequency synthetic jet with elimination of small vortex and confirmation of stable flow. Moreover, performance of multi-array/multi-location synthetic jet can be improved by changing phase angle of multi-location synthetic jet.