AERODYNAMIC ANALYSIS OF NACA 6409 AIRFOIL  IN WIND TURBINE  BY USING PANEL METHOD

Đinh Văn Thìn; Nguyễn Hữu Đức; Lê Quang Sáng

doi:10.34238/tnu-jst.5591

AERODYNAMIC ANALYSIS OF NACA 6409 AIRFOIL IN WIND TURBINE BY USING PANEL METHOD

About this article

Received: 25/02/22 Revised: 12/05/22 Published: 16/05/22

Authors

1. Dinh Van Thin, Electric Power University
2. Nguyen Huu Duc , Electric Power University
3. Le Quang Sang, Institute of Energy Science - Vietnam Academy of Science and Technology

Abstract

This article presents the theoretical basis and applicability of XFLR5 code to conduct aerodynamic analysis of wind turbine airfoil model NACA 6409 at low Reynolds numerical values. The new XFLR5 code is developed based on XFOIL code, which is very popularly used in the field of wing design in the world. The mathematical foundations of XFLR5 include Lifting Line Theory (LLT), Vortex Lattice Method (VLM) and Panel Method (PM). In this study, the PM method will be used to analyze aerodynamic parameters such as lift coefficient C_l, drag coefficient C_d, factor C_l/C_d and pressure coefficient C_p placed on the surface of the NACA 6409 wing sample when operating at different angles of attack. The PM method has a fast analysis time and the obtained results show good agreement with previously published experimental data.

Keywords

LLT Theory; VLM Method; PM Method; XFLR5; NACA 6409 Airfoil; Low Reynolds Number

Full Text:

PDF (Tiếng Việt)

References

[1] M. S. Selig, J. J. Guglielmo, A. P. Broeren, and P. Giguere, “Summary of Low-Speed Airfoil Data-Volume 1”, SoarTech Publication, Virginia Beach, Virginia, 1995.

[2] R. M. Pinkerton, “NACA-report-563 Calculated and Measured Pressure Distributions Over the Midspan Section of the NACA 4412 Airfoil”, Abbort Aerospace, 1937.

[3] Ira H. Abbott, Albert E. Von Doenhoff, and Louis S. Stivers, NACA-report-824 Summary of Airfoil Data, Abbort Aerospace, 1945.

[4] TechWinder, “xflr5 tutorial”, 2019. [Online], Available: http://www.xflr5.tech/xflr5.htm? fbclid=IwAR0XI-jGI2AjxOqbNSB5Vfr0OlP6Xd TWqLGD DtCls BFfv-CGxq92Iyy8KYo. [Accessed April 21, 2022 ].

[5] The National Renewable Energy Laboratory, U.S. Department of Energy, Office of Energy Efficiency and Renewable Energy, “Wind Research-Wind Data and Tools”, 2022. [Online], Available: https://www.nrel.gov/wind/data-tools.html?fbclid=IwAR1jAmmJqGQsRkwnTsWPtk4dz3LbhxcBw1j ITTlEY0h9hP7xicPONuqqS8g. [Accessed April 21, 2022 ].

[6] André Deperrois, “Analysis of foils and wings operating at low Reynolds numbers”, XFLR5 v6.02 Guidelines, 2014.

[7] J. C. Sivells and R. H. Neely, “Method for calculating wing characteristics by lifting line theory using nonlinear section lift data”, NACA Technical Note 1269, April 1947.

[8] M. Drela, “XFOIL: An Analysis and Design System For Low Reynolds Number Airfoils”, MIT Dept. of Aeronautics and Astronautics, Cambridge, Massachusetts, 1989.

[9] M. J. Queijo, NACA-report-1269 Theoritical span load distributions and rolling moments for sideslipping wings of arbitrary plan form in incompressible flow, Abbort Aerospace, 1956.

[10] A. Septiyana, K. Hidayat, A. Rizaldi, and Y. G. Wijaya, “Comparative Study of Wing Lift Distribution Analysis Using Numerical Method,” Jurnal Teknologi Dirgantara, vol. 18, no. 2, pp. 129-139, 2020.

[11] Airfoil Tools, “NACA6409 9% (n6409-il)”, 2022. [Online], Available: http://airfoiltools.com /airfoil/details?airfoil=n6409-il. [Accessed April 21, 2022 ].

DOI: https://doi.org/10.34238/tnu-jst.5591

Refbacks

There are currently no refbacks.



Remember me