Numerical Simulation of NACA 4412 Airfoil to Analysis its Performance Characteristics

Abstract

Investigations on the NACA 4412 airfoil are performed to analyze the influence of ground effect and angle of attack dispersion. The aim is to enhance our comprehension of these phenomena and assess their efficacy in relation to aerodynamic variables. The experimental plan utilizes ANSYS 15 and is based on a three-level factorial design of experiments. The objective is to construct a regression model for the lift to drag (L/D) ratio. There is no correlation observed between ground clearance and angle of attack in relation to both L/D ratio and coefficient of moment. It is revealed by the coefficient of moment, a strong negative impact of component B. Nevertheless, this study solely validates the boundaries that were examined. The model provides us with the optimal L/D ratio and coefficient of moment. At a zero-degree angle of attack, the values are CL 0.53436 and CD 0.00093215, while at an eight-degree AOA, the values are CL 1.4494 and CD 0.0095451. Estimating the value has advantages for designing and testing the NACA 4412 airfoil within specified boundaries.

Keywords

• Turbulent Flow Model
• Pressure Contour
• Velocity Contour
• Velocity Vector
• Angle of Attack

How to cite

Md. Ahatashamul Haque Khan Shuvo, Nabbo Solila Nodee, Md. Atikur Rahman (2024). Numerical Simulation of NACA 4412 Airfoil to Analysis its Performance Characteristics. Sonargaon University Journal, 4(I & II), 1–9.

@article{shuvo20241,
  title   = {Numerical Simulation of NACA 4412 Airfoil to Analysis its Performance Characteristics},
  author  = {Md. Ahatashamul Haque Khan Shuvo and Nabbo Solila Nodee and Md. Atikur Rahman},
  journal = {Sonargaon University Journal},
  volume  = {4},
  number  = {I & II},
  pages   = {1--9},
  year    = {2024},
  issn    = {2518-3125},
  url     = {https://su.edu.bd/journal/volume-4/numerical-simulation-of-naca-4412-airfoil-to-analysis-its-performance}
}