• Journal of Advanced Marine Engineering and Technology
• /
• v.37 no.4
• /
• pp.338-343
• /
• 2013

The Flowfield characteristics of a square prism having a detached splitter plate at the wake region were investigated by visualization of the flow field using PIV. The experimental parameters were the width ratios(H/B=0.5~1.5) of the splitter plate to the prism width and the gap ratios (G/B=0~2) between the prism and the splitter plate. As the results the Strouhal number measured at the wake region of the detached splitter plate was decreased with the width ratio and the gap ratio. The clockwise vortex at the upside of the splitter plate and counterclockwise vortex at the downside were represented, the size of these vortices were increased with the width of the splitter plate. The reverse flow was represented at the wake region of the square prism having a detached splitter plate, the size of this reverse flow was increased with the width of the splitter plate.

• Journal of Aerospace System Engineering
• /
• v.16 no.6
• /
• pp.114-122
• /
• 2022

This paper explores three-dimensional unsteady computational fluid dynamic (CFD) analyses with an overset grid technique to analyse the wake effect created by a rotating propeller on a hand-launched unmanned aerial vehicle (UAV). Additionally, the influence of actual aileron deflection on the equilibrium condition of the rolling moment is examined in various hand-launched take-off conditions. The results of this study demonstrate the importance of initial aileron deflection in increasing the initial rolling stability during the hand-launched take-off process. Furthermore, an aerodynamic database is constructed to rapidly predict the aileron set values required for different take-off speeds and angle-of-attacks.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.36 no.8
• /
• pp.728-733
• /
• 2008

Unsteady aerodynamic analysis of an air-pressure-levitated high-speed ground vehicle moving over the nonplanar ground surface are performed using the boundary-element method. The potential flow solution is included in a time-stepping loop and the wake is captured as part of the solution. When the vehicle moving inside the channel, the lift coefficient and the pitching moment coefficient of the vehicle are increased further because the air trapped by the channel increases the ground effect. In other words, the nonplanar ground surface such as the channel decreases further the longitudinal stability of the vehicle. On the other hand, there is little difference between the ground and the channel in the lateral stability of the vehicle because the lift increment due to the nonplanar ground surface such as the channel takes place on both sides of the wing with the same rate of increase.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.5
• /
• pp.369-374
• /
• 2007

Unsteady aerodynamic characteristics of the wing with flaperon flying over nonplanar ground surface are investigated using a boundary-element method. The time-stepping method is used to simulate the wake shape according to the motion of the wing and flaperon over the surface or in the channel. The aerodynamic coefficient according to the periodic motion of the flaperon is shown as the shape of loop. The rolling moment coefficient of the wing flying in the channel is same as that of the wing flying over the ground surface. The variation range of pitching moment is wider when the wing flies in the channel than over the ground surface. The present method can provide various aerodynamic derivatives to secure the stability of superhigh speed vehicle flying over nonplanar ground surface using the present method.

• 한국전산유체공학회:학술대회논문집
• /
• 2009.11a
• /
• pp.27-33
• /
• 2009

In this paper, the flow past a rotary oscillating circular cylinder is simulated. The high-order and high-resolution numerical schemes with the characteristic boundary conditions are used for the compressible Navier-Stokes equation. The frequencies of rotating oscillation are $0.19\;{\leq}\;S_f\;{\leq}\;0.25$ for the maximum angular $\theta_{max}=10^{\circ}$ and $17^{\circ}$. The flow conditions are Mach number of 0.3 and Reynolds number of 1000. At Lock-on and Non-lock-on region which are defined by the relation between the vortex shedding frequency and the oscillating frequency, the drag and lift coefficient are analyzed.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.3
• /
• pp.57-63
• /
• 2002

지면효과를 받는 와류면의 2차원 비정상 전개를 이산와류법을 사용하여 연구하였다. 와류면이 말리는 정확한 형상을 얻기 위하여, 두 개의 평활기법을 비교하였다. 타원형 하중분포를 가지는 지면가까이에 있는 날개의 후류말림에 대하여 본 연구 방법을 적용하였다. 날개가 지면가까이 비행할 때, 지면효과로 인하여 와류가 날개길이방향으로 이동하였으며 날개익단부근에서 와류면의 늘림운동이 발생하였다.

• Journal of Power System Engineering
• /
• v.4 no.3
• /
• pp.40-47
• /
• 2000

The turbulent flow with wake, reattachment and recirculation flow is very important from the viewpoint of engineering. But that is still difficult because of especially the unsteady problems which are related with the vehicle dynamics and the aerodynamics noise. This paper evaluate LES that can analyze about all fluid flow region including the laminar, transition and turbulent. So we compare the results of LES with those of PIV measurement and Reynolds averaging models. In conclusion, LES predicts flow behavior better than Reynolds averaging models.

• Journal of Power System Engineering
• /
• v.19 no.5
• /
• pp.80-85
• /
• 2015

The unsteady-state, incompressible and three-dimensional large eddy simulation(LES) was carried out to analyze the structure of turbulent flow fields according to the operating loads of three-dimensional small-size axial fan(SSAF). LES shows the best prediction performance in comparison with any other Reynolds averaged Navier-Stokes(RANS) method because static pressure coefficients analysed by LES show a little bit larger than measurements including all flow coefficients. Also, it can be known that the wake of SSAF is divided into from axial flow to radial flow before and behind stall region according to the increase of static pressure through LES analysis.

• Journal of computational fluids engineering
• /
• v.6 no.1
• /
• pp.47-55
• /
• 2001

The transient laminar reacting flows around fuel droplet have been numerically analyzed. The physical models used in this study can account for the variable thermophysical properties and the chemistry is represent by the one-step global reaction model. The present study is focused on the vaporization and ignition characteristics, flame structure including wake flame, transition flame and envelope flame, and interaction between droplets. Special emphasis is given to the triple flame structure and flame stabilization.

• 유체기계공업학회:학술대회논문집
• /
• 2006.08a
• /
• pp.199-202
• /
• 2006

The objective of this study is to propose methods of controlling the wake behind a sphere for drag reduction using the suboptimal control theory and surrogate management framework, respectively. The Reynolds numbers considered is 300 at which the base flow is unsteady planar symmetric. Given the cost function defined as the square of the difference between the target pressure (potential-flow pressure) and real flow pressure on the sphere surface, the suboptimal control makes the flow steady axisymmetric and produces drag reduction. Based on the actuation profile from the suboptimal control, the optimal wavy actuation profile is obtained using the surrogate management framework and produces drag reduction.