• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.8
• /
• pp.37-45
• /
• 2002

A two-dimensional unsteady, inviscid flow solver has been developed for the simulation of airfoil-vortex interactions on unstructured dynamically adapted meshes. The Euler solver is based on a second-order accurate implicit time integration using a point Gauss-Seidel relaxation scheme and a dual time-step subiteration. A vertex-centered, finite-volume discretization is used in conjunction with the Roe's flux-difference splitting. An unsteady solution-adaptive dynamic mesh scheme is used by adding and deleting mesh points to take account of both spatial and temporal variations of the flow field. The effect of vortex interaction on the aeroelastic displacement of an airfoil attached to the idealized two degree-of-freedom spring system is investigated.

• Journal of Ocean Engineering and Technology
• /
• v.11 no.4
• /
• pp.130-140
• /
• 1997

원형주상체 주위의 유동을 규명하기 위해 회류수조에서 원주방향으로 24개의 위치에 대하여 압력을 계측하였으며, laser sheet을 이용하여 유동을 가시화 하였다. Reynolds수가 4800에서 40000인 범위에 대하여 실험을 수행하였다. 또한, 원형단면체 주위의 비정상 층류유동에 대한 Navier-Stokes방정식의 해를 구하는 수치해석기법을 개발하였다. 효과적인 격자배치를 위하여 H와 O-type의 중첩격자를 사용하였고, 이산화 방법으로는 정규격자시스템에서 유한차분법을 적용하였다. 실험과 수치해석결과에서 뚜렷한 와류박리현상을 볼 수 있었으며, 압력계수 (C$_{p}$ ), 항력계수(C$_{D}$), 스트로얼수(St)를 정량적으로 비교하였을 때, 비교적 잘 일치하는 것을 확인하였다.다.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.3
• /
• pp.14-21
• /
• 2006

The unsteady vortex lattice method is used to model twisting and flapping motions of a rectangular flat plate wing. The results for plunging and pitching motions were compared with the limited experimental results available and other numerical methods. They show that the method is capable of simulating many of the features of complex flapping flight. The lift, thrust and propulsive efficiency of a rectangular flat plate wing have been calculated for various twisting angles and reduced frequency with an amplitude of flapping angle($20^{\circ}$). And the effects of the twisting on the aerodynamic characteristics of the flapping wing are discussed by examination of their trends.

• Journal of Navigation and Port Research
• /
• v.37 no.1
• /
• pp.1-7
• /
• 2013

In this paper the developed prediction technique of wave-making resistance performance for a ship attached with a vertical blade had been verified. Numerical analysis program as a prediction technique had been developed using the Rankine source panel method and the vortex lattice method(VLM). The nonlinearity of the free surface conditions was fully taken into account using the iterative method and the trim and the sinkage of the ship were also considered in the numerical analysis program. Panel cutting method was applied to get hull surface panels. Numerical computations were carried out for a 4000TEU container carrier and the vertical blade was attached 6 different locations astern. To investigate the validity of the numerical analysis program the commercial viscous flow field analysis program FLUENT was used to obtain the viscous flow field around the ship and the model test was performed. The model test results were compared with the numerical analysis results.

• Journal of Ocean Engineering and Technology
• /
• v.14 no.2
• /
• pp.36-43
• /
• 2000

In this paper a Vortex Lattice Method is used to predict the performances of a contra-Rotating Propeller. Greeley and Kerwin's(1982) wake model is adopted instead of the exact trailing vortex geometry. The interaction of the two propellers is treated by the sense that the induction of one propeller upon the other propeller is averaged in the circumferential direction . Two single propellers (DTRC 4119 & DTRC 4842) are chosen and compared with the experimental and other numerical results published. Then the computational results for three CRP's (4-0-4 CRP(DTRC 3686+DTRC 3687A) 4-0-5 CRP(DTRC 3686+DTRC 3849) & DTRC CRT(DTRC 5067+DTRC 5068) are compared with the experimental and numerical results published. The interaction of both propellers by the change of inflow velocity and circulation of each propeller is investigated.

• Proceeding of EDISON Challenge
• /
• 2013.04a
• /
• pp.354-359
• /
• 2013

일반적으로 건축물의 설계시 풍동 실험을 통한 풍환경의 평가를 수행하고 있으며, 이는 환경 영향 평가법에서 정한 건축 사업 시행 시 수반되어야 할 자연환경, 생활환경 그리고 사회경제환경의 영향 평가의 일환으로 실시되고 있다. 그러나, 풍동 실험의 경우 여러 가지 현실적 제약조건으로 설계와 실험의 피드백 (Feedback)이 원활하지 못하며, 특히 대상 건축물이 공장과 같이 대기 오염원이 되는 경우 실험은 더욱 어려운 형편이다. 이에 대한 보완책으로 전산 유체 역학을 이용한 건축물의 풍압 해석에 의한 풍하중 추정이나 인접 지형-지물의 영향을 고려한 건축물 주위의 풍환경 평가가 있다. 전산 모사에 의해 풍동 실험의 미비점을 보완하고, 보다 상세한 정보를 확보함으로써 건축물의 구조적 안전성의 증대와 환경 피해 감소를 기할 수 있다. 그러나 복잡한 지형-지물이나 건축물 주위의 풍환경에 대한 전산 모사는 주로 두 가지의 기술적 어려움을 수반하게 되다. 그 중 하나는 고정 경계면을 이루는 형상의 복잡성으로 인해 기존에 많이 이용하고 있는 Body-fitted 격자계를 이용하는 경우, 격자 생성 과정이 매우 복잡하고 어려울 뿐 만 아니라 생성된 격자가 주로 비정렬 (unstructured) 특성을 갖게 되어 수치해석 과정의 효율을 저하시키는 요인이 되며, 격자의 형상도 수치해석의 수렴성을 저하시키는 예가 많다. 다른 어려움으로 풍환경은 전형적인 난류 유동장으로서 난류의 전산 해석은 아직도 해결하지 못한 부분이 많다는 점이다. 이에 본 논문에서는 복잡한 지형-지물이나 건축물의 풍하중과 풍환경의 전산 모사 기술 확보를 위하여 수행중인 연구의 일환으로 물체 형상의 기하학적 복잡성의 극복을 위한 가상경계법 (Immersed Boundary Method)과 난류 유동장의 물리적 엄밀성을 높이기 위한 다와동 모사 (Large Eddy Simulation)을 이용한 물체 형상과 무관한 유동장 해석 기술 개발에 대하여 다루고자 한다. 먼저 최근에 유동 해석에 이용되는 방법인 가상경계법(IBM)은 물체를 포함한 전체 전산 영역을 직교 좌표계에 의해 이산화하고, 유동장내 존재하는 물체의 표면에서의 점착 조건을 만족시키기 위하여 지배 방정식에 적절한 외력을 추가로 고려하는 방법이다. 본 연구에서는 가상경계법을 이용하여 경계층에 위치한 건물 형상의 각진 물체 주위 사이에 형성되는 공동 내부의 비정상 유속 및 압력에 대한 전산 해석을 수행하고, 풍상측 전면에 형성되는 경계층에 의한 영향을 분석하였다.

• The Journal of the Acoustical Society of Korea
• /
• v.40 no.4
• /
• pp.261-269
• /
• 2021

Without any validation of the incompressible assumption, most of previous studies on cavitation flow and its noise have utilized numerical methods based on the incompressible Reynolds Average Navier-Stokes (RANS) equations because of advantage of its efficiency. In this study, to investigate the effects of the flow compressibility on the Tip Vortex Cavitation (TVC) flow and noise, both the incompressible and compressible simulations are performed to simulate the TVC flow, and the Ffowcs Williams and Hawkings (FW-H) integral equation is utilized to predict the TVC noise. The DARPA Suboff submarine body with an underwater propeller of a skew angle of 17 degree is targeted to account for the effects of upstream disturbance. The computation domain is set to be same as the test-section of the large cavitation tunnel in Korea Research Institute of Ships and Ocean Engineering to compare the prediction results with the measured ones. To predict the TVC accurately, the Delayed Detached Eddy Simulation (DDES) technique is used in combination with the adaptive grid techniques. The acoustic spectrum obtained using the compressible flow solver shows closer agreement with the measured one.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.14 no.2
• /
• pp.39-44
• /
• 2006

The unsteady vortex lattice method is used to model lead-lag in flapping motions of a rectangular flat plate wing. The results for plunging and pitching motions were compared with the limited experimental results available and other numerical methods. They show that the method is capable of simulating many of the features of complex flapping flight. The lift, thrust and propulsive efficiency of a rectangular flat plate wing have been calculated for various lead-lag motion and reduced frequency with an amplitude of flapping angle(20o). To describe a motion profile of wing tip such as elliptic, line and circle, the phase difference of flapping and lead-lag motion was changed. And the effects of the motion profile on the aerodynamic characteristics of the flapping wing are discussed by examination of their trends.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.35 no.1
• /
• pp.18-26
• /
• 2007

The steady-state aerodynamic characteristics of wings on the formation flight were analyzed using the Vortex Lattice Method. When two wings were at formation flight, the sectional lift coefficient of a rear wing was increased due to a front wing. The result showed that the lift drag ratio increased as the rear wing were placed downward and decreased as the lateral spacing between wings increased. The difference of lift drag ratio between forward wing and rear wing increase as the aspect ratio of wings increased. When a rear wings and a forward wings placed at the same height, wings on the formation flight had the maximum lift drag ratio. The results showed that the benefit of the formation flight increased as the number of wings on the formation flight increased.

• Journal of the Korean Society for Aviation and Aeronautics
• /
• v.30 no.4
• /
• pp.57-64
• /
• 2022

A study on propllers for unmaned aerial vehicles is conducted using the open softwares. Since the shape of the propeller is closely related to the thurst characteristics of the propulsion system, adopting an appropriate propeller will significantly reflect stable aerodynamic performances. In this study, propellers for unmanned aerial vehicles were modeled by using OpenVSP and Propel for comparison, the thrust characteristics according to the number of blades and the diameter of the propeller were analyzed. In addition, the tendency of thrust characteristics according to various propeller pitch angles was confirmed. Based on the analysis results of this study, the applicability of the propeller shape to the design of the unmanned aerial vehicle was confirmed. It is shownthat the analysis results of this study can be utilized when modeling the propeller shape in research such as a conceptual design of unmanned aerial vehicle. In this case, it should be noted that OpenVSP does not involve the viscous effect of air.