A study on performance of surface modified NACA 2412 airfoil at various Reynolds number and angle of attacks

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NACA, airfoil, angle of attack, Reynolds number.


In the present investigation, aerodynamic performance study of NACA 2412 airfoil with surface modifications for the enhanced optimized aerodynamic characteristics is carried out. Three airfoils were built by introducing the cut at different locations. The present work is a computational analysis of the effect of inward cut on the lower surface of airfoil at 25%, 50%, and 75% chord length. The study parameters include flow separation (or stall), lift, drag, and angle of attack. The model is developed in Ansys design modeler and meshed in ICEMCFD. All three meshed models are simulated at 0o, 40o, 80o, 120o and 16o angle of attacks (AoA) at 60000 and 100000 (1 lakh) Reynolds number. The post processing revealed that, the increase in AoA resulted in increase in lift co-efficient (CL) for all three airfoils at both Reynolds number. The lift coefficient started increasing as the position of cut moved towards the trailing edge. The flow started separating after 12o AoA. It was found that, the airfoil with inward cut at 75% of chord length resulted in attaining highest lift co-efficient when compared to other two airfoils.


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How to Cite

C M, R., R P, Y. S., Hiremath, N., J N, H., Thalekar, T., & D R, D. (2022). A study on performance of surface modified NACA 2412 airfoil at various Reynolds number and angle of attacks. Journal of Mines, Metals and Fuels, 69(12A), 269–275. https://doi.org/10.18311/jmmf/2021/30115
Received 2022-04-28
Accepted 2022-04-28
Published 2022-04-28



O. John E. Matsson, Connor McCain, John Voth, Oral Roberts University, (2017): “Aerodynamic Performance of the NACA 2412 Airfoil at Low Reynolds Number “Connor McCain on 25 August.

A. Ram Krishna Prasad, G. Daison, T. AmuthanSamsudeen, T. Aravind Raj and V. Sri Ram. (2017): He is sincerely thanks to Prof. B. Kanickai Raj, Mr. Ravi Shankar, Mr. G. Sakthivel, JJ College of Engineering and Technology “Flow Simulation on New Airfoils Design”IJSRD - International Journal for Scientific Research & Development, Vol. 4, Issue 12, 2017 | ISSN (online): 2321-0613

Scott Douglas Lindsay, Paul Walsh, Ryerson University, Toronto, Canada. (2018): “Experimental Investigation of Spoiler Deployment on Wing Stall “Open Journal of Fluid Dynamics, 8, 308- 320.

Er. Shivam Saxena, Mr. Rahul Kumar (2015): Department of Aeronautical Engineering, Babu Banarsi Das National Institute of Technology and Management, Lucknow, India “Design of NACA 2412 and its Analysis at Different Angle of Attacks, Reynolds Numbers, and a wind tunnel test” ISSN 2091-2730, Volume 3, Issue 2, March-April.

Sonia Chalia, Manish Kumar Bharti (2017): Assistant professor, Department of Aerospace Engineering, Amity University Haryana Gurgaon, India, “Design and Analysis of Vortex Generator and Dimple over an Airfoil Surface to Improve Aircraft Performance” Vol.3, Issue 4, August 2017, ISSN: 2454-2377.

Yogesh Thawrani and Ajith Kumar S (2018): Department of Mechanical Engineering, Amrita Vishwa Vidyapeetham, Amritapuri, India “Influence of surface temperature on the flow characteristics of NACA 2412 airfoil” Volume 119 No. 12, 71-75 ISSN: 1314-3395.

Md. Tariqul Islamb, Amit M. E. Arefina, M. H. Masudc, (2018): Monjur Mourshedd Department of Mechanical Engineering, Rajshahi University of Engineering and Technology, Rajshahi, Bangladesh “The Effect of Reynolds Number on the Performance of a Modified NACA 2412 Airfoil” doi: 10.1063/1.5044325.

Amit Kumar Saraf, Dr. Mahendra Pratap Singh, Dr. Tejsingh Chouhan (2016): “A Review on Aerodynamic Behaviour of Airfoil when Surface Modified” Volume 7, Issue 3, March, ISSN 2229-5518.