진동하는 2차원 날개 단면 주위에 대한 점성 유동장 계산( Part 1. 동적실속이 없는 경우 )
Computation of Viscous Flows around a Two-dimensional Oscillating Airfoil( Part 1. without Dynamic Stall )
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Abstract
In this paper, numerical calculations are performed to analyze the unsteady flow of NACA airfoil sections. In order to ease the flow computation for the fluid region changing in time, improve the quality of solution and simplify the grid generation for the oscillating foil flow, the computational method adopts a moving and deforming mesh with the multi-block grid topology. The multi-block, structured-unstructured hybrid grid is generated using the commercial meshing software Gridgen V15. The MDM (Moving & Deforming Mesh) and the UDF (User Define Function) function of FLUENT 6 are adopted for computing turbulent flows of the foil in pitching motion. Computed unsteady lift and drag forces are compared with experimental data. In general, the characteristics of unsteady lift and drag of the experiments are reproduced well in the numerical analysis.
참고문헌 (5)
- "공기 강제 주입에 의한 캐비테이션 제어기법 개발" (1999)
- "진동하는 사각날개의 날개끝 와류 구조에 관한 실험적 연구", 43(1), pp.59~67 (2006)
- "피칭 운동하는 NACA0012 날개단면 주위의 비정상 유동 수치해석", pp.281~284 (2004)
- "Hydrofoil Cavitation Improvements with Elatically Coupled Composite Material" (1998)
- "“2-D and 3-D Oscillating Wing Aerodynamics for a Range Angles of Attack Including Stall", pp.~4632 (1994)