• Proceedings of the KSME Conference
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• 2000.11b
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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 Industrial Technology
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• v.22 no.A
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• pp.59-65
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• 2002

The objective of this study is to provide the quantitative and qualitative computational data about the aerodynamic performance of Gurney flap on NACA 00XX airfoils and to show the optimum Gurney flap height for each airfoil. The test was performed on 7 different airfoils from NACA 0006 to NACA0024, which have a 3% chord(=c) thickness interval. For every NACA 00XX airfoil, Gurney flap heights were changed by 0.5% or 0.25% chord interval from 0 to 2.0%c to study their effects. The aerodynamic characteristics of clean and Gurney flap airfoil were compared, and the influences of Gurney flap on each airfoil were compared. As a CFD (Computational Fluid Dynamics) solver, FLUENT, based on Navier-Stokes code, was used to calculate the flow field around the airfoil. The fully-turbulent results were obtained using the standard $k-{\varepsilon}$ two-equation turbulence model. The test results showed that Gurney flap increased the lift coefficient much more than the drag coefficient over a certain range of the lift coefficient, so the lift-to-drag ratio, which is the important index of airfoil performance, was increased. Based on the test results, the relationship between the airfoil thickness and the optimum Gurney flap heights was suggested.

• Archives of Plastic Surgery
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• v.46 no.4
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• pp.324-329
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• 2019

Background Multiple approaches for nipple reconstruction exist, and none is considered superior to all others. The star flap is one of the most popular methods for nipple reconstruction, but gradual height loss is a major concern. We present a new modification of the star flap that incorporates a de-epithelialized dermal flap, along with the associated surgical results. Methods We reviewed the medical records of patients who underwent nipple reconstruction using the modified star flap method. The design was different from the conventional star flap in that the lateral wings were changed into a trapezoidal shape and de-epithelialized dermal flaps were added. The patients were followed up at 2, 4, 6, and 12 months postoperatively, and nipple height was measured. The postoperative nipple height achieved using the modified method was compared with that obtained using the traditional method. Results From February 2013 to June 2017, 32 patients received surgery using the modified star flap, and 18 patients who underwent nipple reconstruction before 2013 comprised the conventional method group. All patients had undergone breast reconstruction with an abdominal tissue-based flap. The mean follow-up period was 14.4 months in the modified method group and 17.3 months in the conventional method group. The mean maintenance of projection at 12 months postoperatively was $56.28%{\pm}18.58%$ in the modified method group, and $44.23%{\pm}14.15%$ in the conventional method group. This difference was statistically significant (P<0.05). Conclusions The modified method using a de-epithelialized dermal flap provides reliable maintenance of projection in patients who have undergone abdominal tissue-based breast reconstruction.

• Proceedings of the KSME Conference
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• 2001.06d
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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.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2001.05a
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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.

• Archives of Plastic Surgery
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• v.36 no.4
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• pp.422-427
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• 2009

Purpose: Breast cancer is second most common cancer in women. Almost of patients with breast cancer treated with mastectomy undergoes breast reconstruction. Nipple reconstruction is an important step in breast reconstruction. Many surgeons have investigated of nipple reconstruction using the flap technique after breast reconstruction with the autologous tissue. The objective of this study is to evaluate the results of nipple reconstruction using the C - V flap technique after breast reconstruction with the only breast expander. Methods: From April 2006 to May 2008, the authors treated 17 patients of nipple reconstruction using C - V flap technique, who were received breast reconstruction with the only breast expander. We have predicted decrease of the size of reconstructed nipple and designed flap a little larger than wanted nipple size. Nipple splint was applied for 4 - 6 months for minimizing decrease of the size of reconstructed nipple. The diameter and height of the reconstructed nipple were measured and patient's satisfaction score was assessed. Results: Mean follow-up duration was 12.5 months. Among the 17 patients, the average absorption rate by height of nipple was 47.0%. Partial necrosis was noted in 1 case, and treated well with conservative management. There was no other significant complications noted. Patient's satisfactory score was assessed by the height, design and location of the nipple. The average of satisfaction score was 85%, 68%, 62% and total average was 83%. Conclusion: The authors experienced 17 patients of nipple reconstruction using the C - V flap technique after breast reconstruction with the only breast expander. The absorption rate of the size of the nipple, complications and patient's satisfactory score of this study were similar to those of nipple reconstruction after breast reconstruction with the autologous tissue. It is expected that nipple reconstruction after breast reconstruction with the only breast expander is safe and reliable. It is considered that a long - term study is necessary.

• Journal of International Society for Simulation Surgery
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• v.4 no.1
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• pp.13-16
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• 2017

Fibular free flap reconstruction is the flap of the choice in long-span mandibular bone reconstruction. The most common disadvantage of the fibular flap is short bone height to install dental implant. Double barrel fibular flap has been tried, however, bulky flap in the oral cavity hinder its use. Titanium reconstruction plate has been used simultaneously with the free fibular flap to stabilize occlusion and to fix the fibular flap. In this study, titanium reconstruction plate was fixed in the lower border of the mandible and the fibular free flap was fixed in the superior border of the titanium plate to improve implant-crown ratio. This new technique improved the longevity of the dental prosthodontics with dental implants.

• 유체기계공업학회:학술대회논문집
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• 2003.12a
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• pp.520-525
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• 2003

A numerical investigation was performed to determine the effect of airfoil on the optimum flap height using NACA0015 Wells turbine. The five double flaps which have 0.5% chord height difference were selected. A Wavier-Stokes code, CFX-TASCflow, was used to calculate the flow field of the Wells turbine. The basic feature of the Wells turbine is that even though the cyclic airflow produces oscillating axial forces on the airfoil blades, the tangential force on the rotor is always in the same direction. Geometry used to define the 3-D numerical grid is based upon that of an experimental test rig. This paper tries to analyze the optimum double flap of Wells turbine with the numerical analysis.

• Archives of Plastic Surgery
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• v.43 no.6
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• pp.529-535
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• 2016

Background The trapezius muscle flap is not usually the first reconstructive option for skin and soft tissue defects in the posterior neck and scalp due to surgeons' unfamiliarity with the surgical anatomy and developments in free tissue transfer techniques. The goals of this study were to describe the clinical use of trapezius flaps in posterior neck and scalp reconstruction, and to investigate the vascular anatomy of trapezius flaps in Asians in order to obtain information facilitating the safe design and elevation of flaps in which most of the muscle is preserved. Methods A retrospective chart review was performed of 10 patients who underwent trapezius muscle flap for posterior neck and scalp defects. We also performed an anatomical study of 16 flaps harvested from 8 preserved Asian adult cadavers and evaluated the main landmarks relevant for trapezius muscle flap. Results In the anatomical study, the mean vertical height from the inferior angle of the scapula to the point at which the superficial cervical artery penetrated the trapezius was $4.31{\pm}2.14cm$. The mean vertical height of the trapezius muscle flap pivot point was $9.53{\pm}2.08cm$ from the external occipital protuberance. Among the 10 flaps, partial necrosis on the overlaid skin graft occurred in 1 patient and postoperative seroma occurred in another patient. Conclusions Vascular variations in the trapezius muscle flap are uncommon in Asians, but when present, such variations appear to have little impact on harvesting the flap or on its circulation. The trapezius muscle flap is a viable alternative for posterior neck and scalp reconstruction.

• Journal of Mechanical Science and Technology
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• v.14 no.9
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• pp.1013-1019
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• 2000

A numerical investigation was performed to determine the effect of the Gurney flap on a NACA 23012 airfoil. A Navier-Stokes code, RAMPANT, was used to calculate the flow field about the airfoil. Fully-turbulent results were obtained using the standard ${\kappa}-{\varepsilon}$ two-equation turbulence model. The numerical solutions showed that the Gurney flap increased both lift and drag. These results suggested that the Gurney flap served to increase the effective camber of the airfoil. The Gurney flap provided a significant increase in the lift-to-drag ratio relatively at low angle of attack and for high lift coefficient. It turned out that 0.6% chord size of flap was the best. The numerical results exhibited detailed flow structures at the trailing edge and provided a possible explanation for the increased aerodynamic performance.