지원사업
학술연구/단체지원/교육 등 연구자 활동을 지속하도록 DBpia가 지원하고 있어요.
커뮤니티
연구자들이 자신의 연구와 전문성을 널리 알리고, 새로운 협력의 기회를 만들 수 있는 네트워킹 공간이에요.
논문 기본 정보
- 자료유형
- 학술저널
- 저자정보
- 저널정보
- 한국항공우주학회 International Journal of Aeronautical and Space Sciences International Journal of Aeronautical and Space Sciences Volume.16 Number.4
- 발행연도
- 2015.12
- 수록면
- 493 - 499 (7page)
이용수
초록· 키워드
오류제보하기
The aerodynamic performance of blunt trailing edge airfoils was investigated. The flow fields around the modified NACA64-418, which consists of the tip blade of the wind turbine and Mexico model of IEA wind, were analyzed. To imitate the repaired airfoil, the original NACA64-418 airfoil, a cambered airfoil, is modified by the adding thickness method, which is accomplished by adding the thickness symmetrically to both sides of the camber line. The thickness ratio of the blunt trailing edge of the modified airfoil, t<SUB>TE</SUB> /t<SUB>max</SUB>, is newly defined to analyze the effects of the blunt trailing edge. The shape functions describing the upper and lower surfaces of the modified NACA64-418 with blunt trailing edge are obtained from the curve fitting of the least square method. To verify the accuracy of the present numerical analysis, the results are first compared with the experimental data of NACA64-418 with high Reynolds number, Re=6×10<SUP>6</SUP>, measured in the Langley low-turbulence pressure tunnel. Then, the aerodynamic performance of the modified NACA64-418 is analyzed. The numerical results show that the drag increases, but the lift increases insignificantly, as the trailing edge of the airfoil is thickened. Re-circulation bubbles also develop and increase gradually in size as the thickness ratio of the trailing edge is increased. These re-circulations result in an increase in the drag of the airfoil. The pressure distributions around the modified NACA64-418 are similar, regardless of the thickness ratio of the blunt trailing edge.
목차
Abstract
1. Introduction
2. Numerical Method
3. Conclusion
References
참고문헌 (13)
참고문헌 신청
[인터넷자원] - J. G. Schepers / / Final report of IEA task 29, Mexnext(phase 1): Analysis of Mexico wind tunnel measurements
[학술대회논문] - W. A. Timmer / 2009 / An overview of NACA 6-digit airfoil series characteristics with reference to airfoils for large wind turbine blades / 47th AIAA Aerospace Science Meeting
[보고서] - J. L. Summers / 1995 / Lift and moment characteristics at subsonic Mach numbers of four 10-percentthick airfoil sections of varying trailing-edge thickness
[보고서] - H. A. Smith / 1950 / Aerodynamic characteristics at Reynolds numbers of 3.0x106 and 6x106 of three airfoil sections formed by cutting off various amount from the near portion of the NACA0012 airfoil section
[학술지(정기간행물)] - K. J. Standish / 2003 / Aerodynamic analysis of blunt trailing edge airfoils / Journal of Solar Energy Engineering 125 : 479 ~ 487
[학술대회논문] - W. A. Timmer / 2009 / An overview of NACA 6-digit airfoil series characteristics with reference to airfoils for large wind turbine blades / 47th AIAA Aerospace Science Meeting
[보고서] - J. L. Summers / 1995 / Lift and moment characteristics at subsonic Mach numbers of four 10-percentthick airfoil sections of varying trailing-edge thickness
[보고서] - H. A. Smith / 1950 / Aerodynamic characteristics at Reynolds numbers of 3.0x106 and 6x106 of three airfoil sections formed by cutting off various amount from the near portion of the NACA0012 airfoil section
[학술지(정기간행물)] - K. J. Standish / 2003 / Aerodynamic analysis of blunt trailing edge airfoils / Journal of Solar Energy Engineering 125 : 479 ~ 487
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