Optimizing the Performance of different Airfoils at Various Angles of Attack through CFD Simulation

Kazim  Ghulam; Faizan  Ali; Athar Ali  Khan Gorar

doi:10.32628/IJSRSET2411145

Authors

Kazim Ghulam College of Electrical and Mechanical Engineering, Harbin Engineering University, Harbin, China Author
Faizan Ali Department of Mechanical Engineering, Quaid-e-Awam University of Engineering, Sciences & Technology, Larkana, Pakistan Author
Athar Ali Khan Gorar Department of Mechanical Engineering, NED University of Engineering and Technology, Karachi, Pakistan Author

DOI:

https://doi.org/10.32628/IJSRSET2411145

Keywords:

Airfoil, Angle of Attack, Lift Coefficient, Drag Coefficient, Simulation Techniques, Turbulence Model, NACA Profiles

Abstract

This study specifically examines the NACA 0012, NACA 4412, and NACA 2412 airfoil profiles using ANSYS FLUENT. By simulating the flow over these airfoils, we can comprehensively explore the impact of the angle of attack on lift and drag coefficients. Notably, the study reveals that the angle of attack directly influences lift force, with a critical angle beyond which the aircraft may stall. Thus, the research underscores the importance of maintaining an optimal angle of attack to avoid turbulence and optimize aircraft performance. The aerodynamics of airfoil shapes play a crucial role in the performance and safety of aircraft. Understanding airflow characteristics over airfoils, particularly concerning the critical angle of attack, is paramount in achieving optimal lift while avoiding stalling. This paper delves into the shift of the separation point on the upper surface of most airfoil shapes, emphasizing the shift from the trailing edge to the leading edge as the angle of attack increases. Stalling becomes a critical concern beyond the critical angle of attack, necessitating comprehensive research to enhance aircraft performance and safety.

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