• 한국항공우주학회지
• /
• 제46권6호
• /
• pp.445-451
• /
• 2018

본 논문에서는 현재 한국항공우주학회 공기역학부문위원회에서 주관하고 있는 EFD-CFD 비교 워크숍의 여러 과제 중 CASE 4 삼각날개(Delta Wing)의 천음속영역의 유동해석 결과를 작성하였다. 풍동실험은 추후에 진행될 예정이며, -5~20도 받음각 영역에서의 CFD 해석을 수행하였다. 해석을 수행한 마하수는 0.7, 0.85, 1.2이다. 삼각날개의 적합한 해석조건을 찾기 위해서 기준격자 크기를 조절하여 격자의존성 해석을 수행하였고, 선택한 격자로 받음각 변화에 따라 양력계수와 항력계수의 경향을 파악하였다.

• 한국군사과학기술학회지
• /
• 제5권3호
• /
• pp.77-86
• /
• 2002

An experimental study of the vortex interaction characteristics of a delta wing/LEX configuration was conducted in a wind tunnel using the micro water droplet and laser beam sheet visualization technique. The main focus of this study was to analyze the effect of the angle of attack and sideslip angle on the vortex interaction and vortex breakdown. These tests were accomplished at angles of attack between $16^{\circ}$ and $28^{\circ}$ and sideslip angle between $0^{\circ}$ and $-15^{\circ}$ at free-stream velocity of 6.2 m/s. Flow visualization data provide a description of the vortex interaction between LEX and wing vortices, and of the vortex breakdown. The introduction of LEX vortex stabilized the vortical flow, and delayed the vortex breakdown up to higher angle of attack. The vortex interaction and breakdown was promoted on the windward side, whereas they are suppressed on the leeward side.

• 한국전산유체공학회:학술대회논문집
• /
• 한국전산유체공학회 2008년도 춘계학술대회논문집
• /
• pp.47-50
• /
• 2008

The unsteady vortical flow over ONERA 70-degree delta wing was simulated using RANS and DES flow solvers on hybrid unstructured meshes. A study of time accuracy is accomplished to determine the effects of time step and number of iteration in pseudo-time stepping on numerical solutions. The grid size test is also performed to demonstrate that DES can be used to capture more accurately the unsteady vortical flow features over RANS simulation.

• 한국가시화정보학회지
• /
• 제5권2호
• /
• pp.56-63
• /
• 2007

Flow visualization and aerodynamic characteristics of delta wings with two different leading edge geometries are investigated by PIV system and wind tunnel balance when the Reynolds number is about based on the freestream velocity and the root chord length. Delta wing models have 65-deg swept angle, and the leading edge shapes are divided into round- and sharp- type. The experimental results indicated that the leading-edge vortex strength and aerodynamic coefficient in the round leading edge are stronger and more, respectively than those in the sharp one. Therefore the flow interactions between vortices and the boundary layer are more desirable or more rapidly swirled in the round-type leading edge.

• 한국항공우주학회지
• /
• 제48권2호
• /
• pp.109-117
• /
• 2020

기존 정렬 격자의 많은 제약 조건들을 완화할 수 있는 patched-grid 알고리즘을 이용하여 효율적으로 정렬 격자계를 구성하였다. EFD-CFD 워크숍의 case 4: 삼각 날개-원통형 동체 형상에 크게 3가지의 접근 방식을 적용하여 기존의 격자 생성 문제점들을 해결하였고, 실험값과 비교하여 검증하였다. 고 받음각 영역에서 표면 압력 분포가 실험값과 다소 차이를 보였다. 마하수의 증가에 따른 피칭 모멘트의 기울기 변화를 분석하였고 이는 tuck under 현상으로 설명할 수 있었다. 초음속 영역에서는 형상 앞에 궁형 충격파가 발생함으로써 삼각익 뒷전까지 양력을 발생시키는 영역이 확장되었다. 또한, 마하수와 받음각에 따라 압력 중심과 무게 중심의 위치를 비교하여 피칭 모멘트의 경향성을 분석하였다.

• 한국전산유체공학회지
• /
• 제20권2호
• /
• pp.73-80
• /
• 2015

Delayed Detached-Eddy Simulation was conducted to investigate surface pressure coefficient distribution and surface pressure fluctuation over an ONERA 70-degree delta wing at a high angle of attack. Time-averaged surface pressure distribution is directly affected by the primary vortices, whereas the pressure fluctuation is influenced by the unsteady fluctuating boundary layer over the surface. And pressure coefficient, velocity, pressure fluctuation, and turbulent kinetic energy were analyzed along the vortex core in order to investigate the process of vortex breakdown. Consequently, strong pressure fluctuations were found where the vortex breakdown was occurred at x~620 mm. The turbulent kinetic energy abruptly increased and followed after the vortex breakdown.

• 한국가시화정보학회지
• /
• 제2권2호
• /
• pp.52-57
• /
• 2004

The development and interaction of vortices over a delta wing with leading edge extension (LEX) was investigated through off-surface flow visualization using micro water droplets and a laser beam sheet. Angles of attack of $20^{\circ}$ and 24$^{\circ}$ were tested at sideslip angles of $0^{\circ}$, $-5^{\circ}$, and $-10^{\circ}$ The flow Reynolds number based on the main-wing root chord was $1.82{\times}10^{5}$. The wing vortex and the LEX vortex coiled around each other while maintaining comparable strength and identity at a zero sideslip. The increase of angle of attack intensified the coiling and shifted the cores of the wing and LEX vortices inboard and upward. By sideslip, the coiling, the merging and the diffusion of the wing and LEX vortices were increased on the windward side, whereas they were delayed significantly on the leeward side. The present study confirmed that the sideslip angle had a profound effect on the vortex structure and interaction of a delta wing with LEX, which characterized the vortex-induced aerodynamic load.

• 한국응용곤충학회지
• /
• 제31권4호
• /
• pp.461-474
• /
• 1992

한국p산 애기물결자나방속을 정리한 결과 1차로 14종이 분류 동정되었다. 이중 1신종, 애기물결자나방, E. bicornuta sp. nov.를 기재 발표하고 이른봄애기물결자나방, E. clavifera, lnoue;삼각무늬애기물결자나방, E. signigera Butler ; 둥근날개애기물결자나방, E. supercastigata lnoue ; 흰애기물결자나방, E. viidaleppi Vojnits ; 실무늬애기물결자나방, E. addictata Dietze ; 긴점애기물결자나방, E. repentina Vojnits et Laever ; 연갈색애기물결자나방, E. antaggregata lnoue ; 너도애기물결자나방, E. consortaria Leech와 긴날개애기물결자나방, E. kamedai Inoue등 9종을 우리나라 미기록종으로 보고한다.

• 해양환경안전학회지
• /
• 제26권1호
• /
• pp.93-102
• /
• 2020

본 연구는 해중림초 주변에서의 감태 포자의 확산 특성에 알아보기 위하여 연구를 수행하였다. 이를 위해 대상해역에서의 현장관측과 EFDC를 활용하여 수치모형실험을 실시하였다. 또한, 앞선 결과를 바탕으로 대상해역에 설치된 해중림초 중 3개종(정삼각뿔형어초, 이중돔형어초, 날개부를가진어초)에 대하여 Flow-3D를 이용한 수치모형실험을 실시하여 실해역 흐름 재현을 통한 포자이동 방향 및 최대 이동거리를 도출하고자 하였다. 연구결과, 정삼각뿔형어초와 이중돔형어초의 경우 포자의 최대 안착지점은 북서쪽 방향으로 10 m, 서쪽방향으로 6 m로 나타났다. 날개부를가진어초의 경우 포자가 해중림초 주변 4m지점에서 최대 안착을 하였다. 이러한 결과는 해중림초 설치시 감태 포자의 확산특성을 고려하여 배치하였을 경우 포자의 이동에 따른 해조류의 부착기질로서의 기능에 대한 효과가 증대될 것으로 판단된다.

• 한국전산유체공학회지
• /
• 제21권3호
• /
• pp.48-54
• /
• 2016

In the present work, numerical simulations were conducted on the scaled model of the BWB type UCAV in the subsonic region using ANSYS FLUENT V15. The prediction method was validated through comparison with experimental results and the effect of the twisted wing was investigated. To consider the transitional flow phenomenon, ${\gamma}$ transition model based on SST model was adopted. The coefficients of lift, drag and pitching moment were compared with experimental results and the pressure distribution and streamlines were investigated. The twisted wing decreases the lift force but increases lift-to-drag ratio through delay of stall and leading edge vortex's movement to the front, also the non-linearity of the pitching moment is decreased.