Linear Strength Vortex Panel Method for NACA 4412 Airfoil

[摘要] The objective of this article is to formulate numerical models for two-dimensional potential flow over the NACA 4412 Airfoil using linear vortex panel methods. By satisfying the no penetration boundary condition and Kutta condition, the circulation density on each boundary points (end point of every panel) are obtained and according to which, surface pressure distribution and lift coefficients of the airfoil are predicted and validated by Xfoil, an interactive program for the design and analysis of airfoil. The sensitivity of results to the number of panels is also investigated in the end, which shows that the results are sensitive to the number of panels when panel number ranges from 10 to 160. With the increasing panel number (N>160), the results become relatively insensitive to it.

[发布机构] 8989 West Rd., Houston; TX; 77064, United States^1

[效力级别] 航空航天工程 [学科分类] 航空航天科学

[关键词] Circulation density;Design and analysis;Interactive programs;Lift coefficient;Sensitivity-of-results;Surface pressure distribution;Two dimensional potential flow;Vortex-panel method