• Advances in aircraft and spacecraft science
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• 제9권2호
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• pp.119-130
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• 2022

Supersonic projectiles like rockets, missiles, or aircraft find various applications in the field of defense. The shape of the wings is mainly designed as wedge shape or delta wings for supersonic vehicles. The study of supersonic flows over the wedges and flat plate delta wings around the large scale of incidence angle is considered in the supersonic projectile. In the present paper, the prime attention is to study the pressure at the nose of the plane wedge over the various Mach number and the various angles of incidence. Ghosh piston theory is used to obtain the pressure distribution analytically, and the results are compared with CFD analysis results. The wedge angle and Mach number are the parameters considered for the research work. The range of wedge angle is 50 to 250, and Mach number is 1.5 to 4.0 are considered for the current research work. The analytical results show excellent agreement with the CFD results. The results show that both the parameters wedge angle and Mach number are influential parameters to vary the static pressure. The static pressure increases with an increase in Mach number and wedge angle.

• 한국안전학회지
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• 제20권2호
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• pp.18-25
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• 2005

This study performed finite element analysis on the pipe bend with various bend angles under loading conditions of internal pressure and combined pressure and bending, to investigate the effect of bend angle on the collapse behavior of pipe bend and on the stress state in the bend region. In the analysis, the pipe bends with bend angle of $5\~90^{\circ}$ were considered, and the bending moment was applied as in-plane closing and opening modes. From the results of analysis, it was found that the collapse moment of pipe bend increases with decreasing bend angle. As the bend angle decreases, also, the equivalent stress at intrados region increases regardless of bending mode. Under closing mode bending especially, the increase in stress at intrados is significant so that the maximum stress region moves from crown to intrados with decreasing bend angle.

• 대한인간공학회지
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• 제25권3호
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• pp.17-24
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• 2006

In this paper, we propose a stress analysis on foot by lifting task attitudes. Maximum force and peak pressure were measured on 8 body regions by Pedar system in order to analysis the stress which is affected by task style and angle on foot when Manual Materials Handling task. As for the peak pressure of the whole foot as to the task height during the lifting task, the height from Knuckle to Shoulder was the least in the peak pressure. Also, as for the maximum force and the peak pressure of the whole foot as to the task angle during the lifting task, it could be seen that the more an angle increases, the stress influencing on a foot jumps. As for the maximum force and the peak pressure by foot region as to the task height in case of the lifting task, the height from Knuckle to Shoulder is indicated the smallest value in the maximum force and the peak pressure, thus there is necessary to attain the work design that considered this. Also, as for the maximum force by foot region as to the task angle in case of the lifting task, 0° tasking is indicated to be least, thus there is necessity to be attained the tasking design in a bid to prevent the existence of an angle. The results of this paper are thought to be helpful to the suitable work design, to the prevention of musculoskeletal disorders related to the lower limbs, and to the design of ergonomic safety shoes.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집E
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• pp.380-385
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• 2001

In the present study, flow characteristics of turbulent oscillatory flow in a square-sectional $180^{\circ}$ curved duct are investigated experimentally. In order to measure wall shear stress and pressure distributions, experimental studies for air flow are conducted in a square-sectional $180^{\circ}$ curved duct by using the LDV system with the data acquisition and the processing system. The wall shear stress measuring point bend angle of the $150^{\circ}$ and pressure distribution of the inlet (${\phi}=0^{\circ}$) to the outlet (${\phi}=180^{\circ}$) at $10^{\circ}$ intervals of the duct. The results obtained from the experimentation are summarized as follows: A wall shear stress value in an inner wall is larger than that in an outer wall, except for the phase angle (${\omega}t/{\pi}/6$) of 3, because of the intensity of secondary flow. The pressure distributions are the largest in accelerating and decelerating regions at the bend angle(${\phi}$) of $90^{\circ}$ and pressure difference of inner and outer walls is the largest before and after the ${\phi}=90^{\circ}$.

• 한국유체기계학회 논문집
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• 제4권4호
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• pp.37-42
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• 2001

In the present study, flow characteristics of turbulent oscillatory flow in an oscillator connected to square-sectional $180^{\circ}$ curved duct are investigated experimentally. In order to investigate wall shear stress and pressure distributions, the experimental studies for air flows we conducted in a square-sectional $180^{\circ}$ curved duct by using the LDV system with the data acquisitions and the processing system. The wall shear stress at bend angle of the $150^{\circ}$ and pressure distribution of the inlet (${\phi}=0^{\circ}$) to the outlet (${\phi}=180^{\circ}$) by $10^{\circ}$ intervals of the duct are measured. The results obtained from the experiment are summarized as follows : wall shear stress values in the inner wall we larger than those in an outer wall, except for the phase angle (${\omega}t/{\pi}/6$) of 3, because of the intensity of secondary flow. The pressure distributions are the largest in accelerating and decelerating regions at the bend angle(${\phi}$) of $90^{\circ}$ and pressure difference of inner and outer walls is the largest before and after the ${\phi}=90^{\circ}$.

• 한국지반공학회논문집
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• 제33권11호
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• pp.59-72
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• 2017

본 연구에서는 사질토 뒷채움재의 캔틸레버 옹벽에서 뒷굽 끝단 연직면에 작용하는 주동토압을 산정하는 방법을 제안하였다. 캔틸레버 옹벽에서 뒷굽길이에 따른 전단 영역의 변화는 벽체의 벽마찰력, 뒷채움 경사에 따라 뒷굽 끝단 연직면에 작용하는 주동토압에 영향을 준다. 뒷굽길이에 따라 변하는 파괴면각도를 가정하여 토압을 산정하는 한계평형법은 적용하기에 매우 복잡하므로 본 연구에서는 한계해석법을 사용하여 토압을 구하였다. 한계해석법으로 뒷굽길이에 따라 실제 파괴면각도가 고려된 토압을 정확히 산정하고, 이로부터 뒷굽 끝단 연직면에 작용하는 수평토압과 연직토압을 분석하였다. 본 연구결과에 의하면, 뒷굽길이가 짧아짐에 따라 내측 파괴면 경사각은 이론식보다 증가한 반면에 외측 파괴면 경사각은 영향을 받지 않았다. 뒷굽 끝단의 연직면에 작용하는 배면마찰각은 지표면 경사각과 벽면마찰각 사이의 값을 나타내었으며, 주동토압 또한 감소하였다. 최종적으로 상대적인 뒷굽길이와 뒷굽 끝단의 연직면에 작용하는 마찰각(연직토압/수평토압의 비)의 상관관계를 사용함으로써 Coulomb 토압을 간편하게 산정할 수 있도록 하였다.

• 한국지반공학회:학술대회논문집
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• 한국지반공학회 1999년도 가을 학술발표회 논문집
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• pp.489-496
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• 1999

The safety of a structure can be improved by applying the three dimensional passive earth pressure. Because the three dimensional passive earth pressure is much larger than the two dimensional passive earth pressure and it is determined by the size(width B and height H) and the wall frictional angle of the resistant wall. Therefore, the three dimensional passive resistance behavior was studied through the model tests in sandy ground, where the size of the resistant wall and the wall frictional angle were varied. The results show that three dimensional passive earth pressure is 1.1∼3.4 times larger than that of the two dimensional value depending on the wall size and the wall friction.

• 한국분무공학회지
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• 제8권4호
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• pp.17-23
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• 2003

To find suitable injection pressure, ultra high pressure impinging spray characteristics were investigated with a impinging distance and a impinging angle by using high pressure injection system. As impinging distance was increased, spray penetration was decreased but spray height was increased. For increase of injection pressure, spray penetration and spray height were increased until 2,500bar. But over this injection pressure region, the rate of increase was decreased suddenly.

• 한국항공우주학회지
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• 제45권7호
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• pp.531-538
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• 2017

비행속력 및 받음각과 옆미끄럼각을 측정할 수 있는 플러시 대기자료측정장치를 소형의 무인항공기를 대상으로 설계/제작하였다. 동체 노즈콘 표면에 4개 압력 측정점과 5개 압력 측정점의 2가지 타입으로 플러시 압력공들을 만들었다. 플러시 압력공의 교정 압력 데이터는 전기체를 전산유체해석 코드로 계산하여 구축하였다. 교정압력 데이터로부터 받음각, 옆미끄럼각, 전압계수, 정압계수는 4차 다항식으로 표현하고, 최소자승법으로 교정계수 행렬을 구하였다. 비행시험 결과 4개 플러시 압력공 및 5개 플러시 압력공을 이용하여 예측된 비행속력, 받음각과 옆미끄럼각은 비교를 위해 장착한 5-압력공 프로브로 예측된 것과 잘 일치하였으며, 특히 4개의 압력공으로 5개 압력공과 거의 동일한 결과를 얻을 수 있었다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.131-134
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• 2002

Compressible gas flow through a convergent-divergent nozzle is choked at the nozzle throat under a certain critical pressure ratio, and then being no longer dependent on the pressure change in the downstream flow field. In practical, the flow field at the divergent part of the critical nozzle can affect the effective critical pressure ratio. In order to investigate details of flow field through a critical nozzle, the present study solves the axisymmetric, compressible, Wavier-Stokes equations. The diameter of the nozzle throat is D=8.26mm and the half angle of the diffuser is changed between $2^{\circ}\;and\;10^{\circ}$ Computational results are compared with the previous experimental ones. The results obtained show that the divergence angle is significantly influences the critical pressure ratio and the present computations predict the experimented discharge coefficient and critical pressure ratio with a good accuracy. It is also found that a nozzle with the half angle of $4^{\circ}$ nearly predicts the theoretical critical pressure ratio.