• 한국항공우주학회지
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• 제35권1호
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• pp.18-26
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• 2007

날개들이 편대를 이루면서 비행하는 경우의 정상상태 공력특성에 대하여 와류격자법을 이용하여 해석하였다. 2개의 날개가 편대 비행 상태에 있을 때, 선도 날개에 의하여 후방 날개의 부분 양력계수가 높아짐을 알 수 있었다. 3개 이상의 날개를 일렬 및 V자편대 배치하여 양항비에 대하여 해석하였는데, 날개가 편대의 후방에 위치할수록 커지고, 가로 간격이 벌어질수록 작아짐을 알 수 있었다. 가로세로비가 증가할수록 전방 날개와 후방 날개의 양항비 차이가 커짐을 알 수 있었다. 후방 날개의 높이를 변화시켰을 경우, 같은 높이에서 최대 양항비를 나타내었다. 3개, 9개, 15개의 날개를 편대 비행했을 경우 날개 수가 많아질수록 편대 비행의 이득이 증가함을 알 수 있었다.

• Maxillofacial Plastic and Reconstructive Surgery
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• 제21권4호
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• pp.376-381
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• 1999

A variety of materials and procedures such as sinus floor elevation, sinus-lift graft, inlay bone graft using Le Fort I osteotomy, and onlay graft have been used to create adequate bone volume in the maxillary sinus for placement of endosseous implants in the posterior atrophic maxilla. Because of the frequent lack of bone in the posterior maxilla, sinus lift procedure has become a commonly practiced treatment modality. The 138 endosseous implants of 36 patients with sinus augmentation procedures performed in Korea University Hospital from January 1991 to December 1998 were summarized and analysed. The result of this study were as follows: 1. Age ranged from 39 to 57, with a mean of 50.7. 2. The mean survival rate for 138 implants with maxillary sinus lift procedure was 80.4%. 3. There was no corelationship between the fixture length, width and the survival rate. 4. The result showed that the healing period for 8-12 months was necessary if the residual alveolar bone height was less than 5mm. 5. Autogenous iliac corticocancellous block graft showed the most favorable survival rate(95%).

• 한국마린엔지니어링학회:학술대회논문집
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• 한국마린엔지니어링학회 2001년도 춘계학술대회 논문집
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• pp.58-62
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap. height using NACA 0006, 0009, 0012, 0015, 0018, 0021 and 0024 airfoils. The six flaps which have 0.5% chord height difference were used. A Navier-Stokes code, FLUENT, was used to calculate the flow field of the airfoil. The code was first tested as a benchmark by modelling flow around a NACA 4412 airfoil. Predictions of local pressure coefficients are found to be in good agreement with the result of the experimental result. For every NACA 00XX airfoil, flap heights ranging from 0.0% to 2.5% chord were changed by 0.5% chord interval and their effects were also studied. Representative results from each case are presented graphically and discussed. It is concluded that this initial approach gives a promise for the future development of wind turbine optimum design.

• Journal of the Korean Association of Oral and Maxillofacial Surgeons
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• 제33권5호
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• pp.511-517
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• 2007

Purpose: The aim of this study is to determine whether a difference in the amount of bone graft material is needed between edentulous patients and dentulous patients and to calculate the amount of augmentation for a sinus lift procedure. Methods: 19 patients(20 sinuses) were included to measure maxillary sinus volume. Facial CT scanning was performed using MX 8000 IDT CT devices(Philips, USA). And it was used for IDLvm(The IDL Virtual Machine) 6.0, CT Volume Analyzer Ver 2.3 program to measure maxillary sinus volumes Results: At edentulous patients, volumes(mean${\pm}SD$) of the inferior portion of the sinuses were $0.56{\pm}0.13cm^3$(5mm height), $2.35{\pm}0.57cm^3$(10mm height), $4.85{\pm}1.10cm^3$(15mm height). At dentulous patients, volumes(mean${\pm}SD$) of the inferior portion of the sinuses were $0.41{\pm}0.18cm^3$(5mm height), $1.76{\pm}0.42cm^3$(10mm height), $3.80{\pm}0.84cm^3$ (15mm height). A significant correlation was found between augmentation height(5mm, 10mm, 15mm) and the calculated sinus volume.(p=0.027, p=0.018, p=0.044) Conclusions: A significant correlation was found between augmentation height(5mm, 10mm, 15mm) and the calculated sinus volume. Detailed preoperative knowledge of sinus lift augmentation volume is helpful in determining the appropriate amount of the bone graft material.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2001년도 춘계학술대회논문집D
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• pp.1014-1019
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• 2001

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA 00XX and 44XX airfoils. The six flaps which have 0.5% chord height difference were selected. A Navier-Stokes code, FLUENT, was used to calculate the flow field of the airfoil. The code was first tested as a benchmark by modelling flow around a NACA 4412 airfoil. Predictions of local pressure coefficients are found to be in good agreement with the result of the experimental result. For every NACA 00XX and 44XX airfoil, flap heights ranging from 0.0% to 2.5% chord were changed by 0.5% chord interval and their effects were also studied. Representative results from each case are presented graphically and discussed. It is concluded that this initial approach gives an idea for the future development of the wind turbine optimum design.

• 한국콘텐츠학회논문지
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• 제15권5호
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• pp.18-26
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• 2015

본 논문에서는 다양한 무대연출이 가능한 전(Omni)방향 이동무대와 수직 상승 무대로 구성된 복합형 무대 시스템의 설계 및 제어 방법에 대해 제안하였다. 복합 무대 시스템은 전후/좌우/회전 등 3 자유도 모션의 이동무대와 1 자유도 상/하 모션의 상승 무대 등 총 4 자유도 동작이 가능하도록 개발 되었다. 이동무대는 2개의 구동 휠과 조향 휠 구조로 설계하여 기존 차동 방식의 이동무대에 비해 기동성을 높였으며, 상승무대는 전고대비 수식 상승비가 10배 이상 가능하도록 맞물림 방식의 구조로 설계하였다. 또한, 공연연출에 필요한 모션 구현을 위해 경로계획 방법과 계획된 경로를 추종하기 위한 제어방법에 대해서도 제안하였다. 그리고 복합형 무대 시스템의 수평 이동 및 수식 상승 등 복합 모션 실험을 통해 그 성능을 검증하였으며, 공연 공간 디자인 도록을 제시하여 개발된 시스템이 공연에서 다양한 연출에 활용이 가능함을 보였다.

• 한국해양공학회지
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• 제9권2호
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• pp.71-74
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• 1995

A numerical model capable of simulating a 2-D airfoil flying over in the vicinity of the waves is discussed. Instead of treating the problem as a heaving oscillation one above the rigid flat wall, sources are distributed on the prescribed wave profile. The wave deformation due to the airfoil is assumed to be negligible and treated as a rigid undulated wall. The source and vortex are distributed on the surface of the foil. It is found that the variation of $C_L$ with wave steepness in severe and that the lift variation due to waves decreases as the wing height above the water surface increases.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2000년도 추계학술대회논문집B
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• pp.568-572
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• 2000

A numerical investigation was performed to determine the effect of airfoil thickness on the optimum Gurney flap height using NACA 00XX series airfoils. Seven airfoils which have 3% chord thickness difference were used. These were NACA 0006, 0009, 0012, 0015, 0018, 0021, and 0024. A Navier-Stokes code, FLUENT, was used to calculate the flow field about airfoil. The fully turbulent results were obtained using the standard $k-{\varepsilon}$ two-equation turbulence model. To provide a check case fur our computational method, numerical studies for NACA 4412 airfoil were made and compared with already existing experimental data for this airfoil by Wadcock. For every NACA 00XX airfoil, Gurney flap heights ranging from 0.5% to 2.0% chord were changed by 0.5% chord interval and their effects were studied. With the numerical solutions, the relationship between $(L/D)_{max}$ and airfoil thickness as a function of flap height and the relationship between $(L/D)_{max}$ and flap height as a function of airfoil thickness were investigated. The same relationship for $(C_l)_{max}$ also were shown. From these results, the optimum flap size for each airfoil thickness can be determined and vice versa.

• Journal of Periodontal and Implant Science
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• 제49권4호
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• pp.237-247
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• 2019

Purpose: To analyze the maxillary sinus anatomy over edentulous ridges in the bilateral posterior maxillary area in Taiwanese patients using cone-beam computed tomography (CBCT). Methods: In total, 101 anatomical sites from 61 patients, including 32 premolar and 69 molar regions, were analyzed using CBCT. Measurements were made of the width and height of edentulous ridges, the thickness of the lateral wall of the maxillary sinus, and the presence of a sinus septum and the posterior superior alveolar artery (PSAA). A statistical analysis of the measurements was performed, and correlations among the measurements were assessed. Results: The average ridge width was $10.26{\pm}3.16mm$, with a significantly greater ridge width in the second molar region than in the premolar region. The mean residual ridge height was $8.55{\pm}4.09mm$, and ridge height showed an opposite trend from ridge width for the premolar and molar regions. A sinus septum was present at 5.9% of the sites, and the PSAA was observed in 24.5%. The average thickness of the lateral wall of the maxillary sinus was $2.08{\pm}0.94mm$, with no significant difference between the tooth position and lateral wall thickness. Conclusions: This study presents the anatomical features of the maxillary sinus, which should be considered in sinus lift procedures for implant placement, in the Taiwanese population. The use of CBCT is recommended to avoid intraoperative complications.

• Maxillofacial Plastic and Reconstructive Surgery
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• 제20권2호
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• pp.166-172
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• 1998

Missing of the upper posterior dentition can cause alveolar bone resorption & pneumatization of Maxillary sinus wall, which makes traditional implant placement impossible, The solution includes various methods to the posterior maxilla to provide adequate bone support for implant installation and long-term survival. -- sinus floor elevation, sinus-lift graft, inlay graft using LeFort I osteotomy, onlay graft, This is a clinical Sr. retrospective study on implant surgery & prosthodontic restoration with upper edentulous posterior jaw from Jan. 1990. to Jun. 1997 at implant clinic of Chonbuk National University Hospital. The results obtained were as follows: 1. Six hundred ninety-nine implants were placed on upper posterior jaw of two hundred seventeen patients, among them one hundred sixty-five implants were placed in forty-four patients with sinus lift. 2. The height of the remained alveolar bone was classified on the base of Misch's concept. This included seventy-nine SA-1s, ninety-seven SA-2s, sixty-five SA-3s and sixty SA-4s. 3. Ninety percent of implants were successfully integrated in non-grafted area and eighty-seven percent of implants were successully integrated in sinus lift area.