Characterization of NACA 2412 and NACA 4412 airfoils: Effects of angle of attack on aerodynamics coefficients

Abstract

The angle of attack plays a pivotal role in determining the performance of an aircraft wing, a critical component of its overall design. This angle, defined as the angle between the chord line of the wing and the relative wind direction, has a profound impact on the lift and drag forces experienced by the wing. When the angle of attack is low, the wing generates lift with minimal drag. However, at higher angles of attack, the wing encounters increased drag and may reach a stall condition. Understanding the influence of the angle of attack on an aircraft wing is crucial in both design and operation, significantly impacting the aircraft’s capabilities in takeoff, climb, navigation, and landing. Therefore, a comprehensive comprehension of the relationship between the angle of attack and wing performance is imperative for ensuring safe and efficient aircraft operation. This study is dedicated to elucidating the effect of the angle of attack on aircraft performance, focusing on the variation in aerodynamic coefficients for two distinct airfoils. Employing Computational Fluid Dynamics (CFD) analysis via SolidWorks, the research examines NACA airfoil types, specifically NACA 2412 and NACA 4412, each featuring different cambers. The selected angles of attack for the investigation range from 0° to 20°, with a constant flow rate of 43 m/s. The findings reveal that the NACA 2412 airfoil exhibits a higher lift-to-drag ratio near to 20 compared to 6 in NACA 4412 airfoil. This insight provides valuable information for optimizing the aerodynamic performance of aircraft wings, contributing to the enhancement of overall efficiency and safety in aviation.

Keywords

• Angle of Attack
• Drag Coefficient
• Lift Coefficient
• NACA 2412
• NACA 4412

References

1. [1] Oukassou K, El Mouhsine S, El Hajjaji A, Kharbouch B. Comparison of the power, lift and drag coefficients of wind turbine blade from aerodynamics characteristics of NACA0012 and NACA2412. Proc Manufact 2019;32:983990. [CrossRef]
2. [2] Kulshreshtha A, Gupta SK, Singhal P. FEM/CFD analysis of wings at different angle of attack. Mater Today Proc 2020;26:16381643. [CrossRef
3. [3] Abood YA, Abdulrazzaq OA, Habib GS, Haseeb ZM. Determination of the Optimum Aerodynamic Parameters in the Design of Wind Turbine Using COMSOL Multiphysics Software. Iraqi J Indust Res 2022;9:7785. [CrossRef
4. [4] Rao YSR, Manohar MS, Praveen SS. CFD simulation of NACA airfoilsat various angles of attack. IOP Conf Ser Mater Sci Engineer 2021;1168:012011. [CrossRef
5. [5] Hasan SM, Islam SM, Haque M. Comparison of aerodynamic characteristics of NACA 0012 and NACA 2412 airfoil. IJRASET 2021;9:20372045. [CrossRef
6. [6] Merryisha S, Rajendran P, Khan SA. CFD Simulation of NACA 2412 airfoil with new cavity shapes. Adv Aircraft Spacecraft Sci 2022;9:131148.
7. [7] Nguyen MT, Nguyen NV, Pham MT. Aerodynamic analysis of aircraft wing. VNU J Sci Math Physics 2015;31:6875.
8. [8] Shivalingaswamy HB, Panshetty S, Shreyas HS, Sanjay V, Vinayaka N. CFD Analysis of Different Airfoils at Various Angles of Attack. EasyChair No. 10412. Available at: https://easychair.org/publications/preprint/H982/open. Accessed Oct 11, 2024.

9. [9] Matsson JE, Voth JA, McCain CA, McGraw C. Aerodynamic performance of the NACA 2412 airfoil at Low Reynolds Number. ASEE Annual Conference & Exposition, New Orleans, Louisiana, 2016.
10. [10] Ganesh Ram RK, Cooper YN, Bhatia V, Karthikeyan R, Periasamy C. Design Optimization and Analysis of NACA 0012 Airfoil using Computational fluid dynamics and Genetic algorithm. Appl Mech Mater 2014;664:111116. [CrossRef
11. [11] Islam MT, Arefin AM, Masud MH, Mourshed M. The effect of Reynolds number on the performance of a modified NACA 2412 airfoil. AIP Conf Proc 2018;1980:040015. [CrossRef
12. [12] Noronha NP, Krishna M. Aerodynamic performance comparison of airfoils suggested for small horizontal axis wind turbines. Mater Today Proc 2021;46:24502455. [CrossRef
13. [13] Singh RK, Ahmed MR, Zullah MA, Lee YH. Design of a low Reynolds number airfoil for small horizontal axis wind turbines. Renew Energy 2012;42:6676.‏ [CrossRef
14. [14] Yakhot V, Orszag SA, Thangam S, Gatski TB, Speziale CG. Development of turbulence models for shear flows by a double expansion technique. Physics Fluids A Fluid Dynamics 1992;4:15101520. [CrossRef
15. [15] Ravi D, Rajagopal TKR. Numerical investigation on the effect of slit thickness and outlet angle of the bladeless fan for flow optimization using CFD techniques. J Therm Engineer 2023;9:279296. [CrossRef
16. [16] Karasu İ, Açıkel HH, Koca K, Genç MS. Effects of thickness and camber ratio on flow characteristics over airfoils. J Therm Engineer 2020;6:242252. [CrossRef
17. [17] Hussein EQ, Azziz HN, Rashid FL. Aerodynamic study of slotted flap for NACA 24012 airfoil by dynamic mesh techniques and visualization flow. J Therm Engineer 2021;7:230239. [CrossRef
18. [18] Mohammed MA, Husain MA. Numerical simulation of aerodynamic performance of the wing with edge of attack and sinusoidal escape. J Therm Engineer 2024;10:697709. [CrossRef
19. [19] Korkan KD, Camba J III, Morris PM. Aerodynamic data banks for Clark-Y, NACA 4-digit and NACA 16-series airfoil families, 19860021221. Available at: https://ntrs.nasa.gov/api/citations/19860021221/downloads/19860021221.pdf. Accessed Oct 11, 2024.
20. [20] Soh ZP, Al-Obaidi ASM. Numerical analysis of the shape of dimple on the aerodynamic efficiency of NACA 0012 airfoil. Proceedings of the 6th EURECA 2016 Conference (Paper Number 2ME25), Kuala Lumpur, Malaysia, 2016. pp. 67.
21. [21] Madenci E, Guven I. The Finite Element Method and Applications in Engineering Using ANSYS®. New York: Springer; 2006. pp.1535.
22. [22] Kim J, Park YM, Lee J, Kim T, Kim M, Lim J, et al. Numerical investigation of jet angle effect on airfoil stall control. Appl Sci 2019;9:2960. [CrossRef
23. [23] Kundu PK, Cohen IM, Dowling DR. Fluid mechanics. Cambridge, MA: Academic Press; 2015.
24. [24] Feng LH, Choi KS, Wang JJ. Flow control over an airfoil using virtual Gurney flaps. J Fluid Mech 2015;767:595626. [CrossRef