COMPARISON OF NACA 0012 AND KFM-4 WING PROFILES FOR HIGH SPEED UNMANNED AERIAL VEHICLES

Year 2024, Volume: 7 Issue: 2, 72 - 76, 31.12.2024

Muktedir Gözüm , Cevat Ozarpa

https://doi.org/10.70858/tijmet.1402218

Abstract

The aim of the study is to present an analysis and comparison of airflow over KFm-4 (Kline-Fogleman) and NACA 0012 airfoils. The result of this comparison is to evaluate the suitability of using it in high-speed unmanned aerial vehicles. While increasing the speed of high-speed unmanned aerial vehicles, it will be important to fly more stable, have better maneuverability, reduce the drag force and delay separation. The calculations were obtained by performing computational fluid dynamics analyses. Since two-dimensional and three-dimensional airfoils showed equivalent results, two-dimensional airfoils were used. Analysis was conducted under conditions of a low Reynolds number, with a consistent velocity at Mach 0.6 and a zero-degree angle of attack. To validate the precision of the outcomes, a series of tests were executed, involving variations in grid size or node configurations. With the increase in the number of nodes, the transport coefficient exhibited a rising trend; however, upon reaching 305,100 nodes, further increase in nodes did not lead to any significant change in the transport coefficient. As a result, a transport coefficient value of 0.10103 was obtained for the NACA 0012 profile, while a transport coefficient value of 0.072038 was obtained for the KFm-4 profile. Thus, it was concluded that it would be more appropriate to use the NACA 0012 profile in high-speed unmanned aerial vehicles.

Keywords

Kline-Fogleman, NACA 0012, High Speed UAV, Symmetrical Airfoil, CFD Analysis

Supporting Institution

Karabük Üniversitesi

Project Number

KBÜBAP-22-YL-071

Thanks

This article was supported by Karabuk University Scientific Research Projects Coordination Office with the project number KBÜBAP-22-YL-071. I would like to thank Karabuk University Scientific Research Projects Coordination Office for its support. I would like to express my endless gratitude to Dr. Cevat ÖZARPA, who showed interest and support in the planning, research, execution and formation of this thesis study and made a great contribution with his guidance and information.

References

• Kowaleczko, G., Stryczniewicz, W., Szczepaniak, R., Bąbel, R., and Grzywacz, A., The effect of using the Kline-Fogleman modification upon the coefficient characteristics of aerodynamic forces in the airfoil, Journal of KONES Powertrain and Transport, 2018, 25(2): 349–356
• Fogleman, F., Kline, R., Airfoil for aircraft having improved lift generating device, US patent No. US4046338A, United States Patent and Trademark Office, 1977
• Fincham, J.H., and Friswell, M.I., Aerodynamic optimisation of a camber morphing aerofoil, Aerosp. Technol., 2015, 43, 245–255
• Lei, J., Guo, F., and Huang, C., Numerical study of separation on the trailing edge of a symmetrical airfoil at a low Reynolds number, Chinese J. Aeronaut., 2013, 26(4): 918–925,
• Kabir, M.A., Islam, M., Akib, Y.M., and Hafiz, A., Comparison between two Kline–Fogleman modified (KFm) based stepped airfoils for better aerodynamic performance, International Conference on Innovation in Engineering and Technology, Dhaka, Bangladesh, 2019
• Saraf, A.K., Singh, M.P., Chouhan T.J., Aerodynamic analysis of NACA 0012 airfoil using CFD, International Journal of Mechanical and Production Engineering, 2017, 5(12): 21-25
• ANSYS Inc., ANSYS Fluent Tutorial Guide 18, 2018, 229-265
• Z., Li, P., Zhang, T., Pan, and Q., Li, Study on effects of thickness on airfoil-stall at low Reynolds numbers by cusp-catastrophic model based on GA (W) -1 airfoil, Chinese J. Aeronaut., 2020, 33(5): 1444–1453
• Zhen, T.K., Zubair, M., and Ahmad, K.A., Experimental and Numerical Investigation of the Effects of Passive Vortex Generators on Aludra UAV Performance, Chinese J. Aeronaut., 2011, 24(5): 577–583
• Soğukpınar, H., Uçak Kanatlarinda En İdeal Hücum Açisini Bulmak İçin 4 Rakamli Naca 00xx Kanat Profillerinin Nümerik Analizi, Uludağ Üniversitesi Mühendislik Fakültesi Dergisi, 2017, 22(1), 169-178
• Simons, M., Model Aircraft Aerodynamics, 4 th., Adelaide: Argus Books, 1994