NACA16-020 익형의 단면을 갖는 날개 끝 와류 현상에 대한 3 차원 난류유동 해석 (Three-Dimensional Analysis of the Turbulent Wingtip Vortex Flows of a Wing with NACA 16-020 Airfoil Section)

서지정보

· 발행기관 : 대한기계학회
· 수록지 정보 : 대한기계학회논문집 B / 33권 / 8호 / 635 ~ 642페이지
· 저자명 : 정남균

초록

The three-dimensional turbulent wingtip vortex flows have been examined in the present study by using the commercial code FLUENT. The standard k-ε model is used as a closure relationship. The wing is constructed by using
an elliptic body whose aspect ratio is 3.8 and the NACA 16-020 airfoil section. The simulations for various angle attack (α=0°, 5°,and 10°) are carried out. The effect of Reynolds number is also investigated in this study. As the angle
attack increases, the wingtip vortex becomes stronger. However, the relative vortex strength to inlet velocity decreases as Reynolds number increases.

영어초록

The three-dimensional turbulent wingtip vortex flows have been examined in the present study by using the commercial code FLUENT. The standard k-ε model is used as a closure relationship. The wing is constructed by using
an elliptic body whose aspect ratio is 3.8 and the NACA 16-020 airfoil section. The simulations for various angle attack (α=0°, 5°,and 10°) are carried out. The effect of Reynolds number is also investigated in this study. As the angle
attack increases, the wingtip vortex becomes stronger. However, the relative vortex strength to inlet velocity decreases as Reynolds number increases.

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