NACA 4412 AIRFOIL CHAEACTERSTICS ANALYSIS

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1. Introduction: Airfoil: An airfoil is a streamlined shape designed to generate lift when air flows over it. It is typically used in the wings of aircraft, propellers, and other aerodynamic surfaces. The primary purpose of an airfoil is to create a pressure difference between its upper and lower surfaces, resulting in lift that supports the weight of the aircraft or provides thrust. Drag : Drag is the force that acts parallel to the direction of the airflow and opposes the motion of the airfoil through the air. Lift: Lift is the force that acts perpendicular to the oncoming airflow or relative wind. It is generated by the pressure difference between the upper and lower surfaces of an airfoil. Camber: The curvature of the airfoil's upper and lower surfaces. It affects the lift characteristics. Chord Line: An imaginary straight line connecting the leading and trailing edges. Thickness: The distance between the upper and lower surfaces of the airfoil, affecting drag and structural strength. Lift Coefficients: The lift coefficient is a measure of the lift generated by an airfoil relative to the air density, the velocity of the airflow, and the surface area of the airfoil. Drag Coefficients : The drag coefficient is a measure of the drag force experienced by an airfoil relative to the air density, the velocity of the airflow, and the surface area

2. Introduction Airfoil Design: the NACA 4412 airfoil was meticulously designed using SolidWorks by implementing NACA coordinate systems. This approach ensured precise control over the airfoil's shape, allowing for detailed customization and optimization. NACA 4412 : The NACA 4412 airfoil, with its moderate camber, is widely used for its balanced lift and drag. As the angle of attack ( AoA ) increases, lift also increases until stall occurs due to flow separation. At high Reynolds numbers, typical in high-speed conditions, the transition from laminar to turbulent flow becomes more pronounced, impacting aerodynamic efficiency. Aerodynamic Efficiency: Wind turbine blade efficiency is critically influenced by the aerodynamic properties of the airfoil used. The choice of airfoil directly impacts lift and drag forces, which are crucial for the system's overall performance. CFD Simulations: Using Computational Fluid Dynamics (CFD), the airfoil's performance is simulated for angles of attack ranging from 0° to 45 in 3° increments, under high Reynolds conditions. Analysis Parameters: Key aerodynamic parameters such as static pressure distribution, velocity distribution, lift coefficient, drag coefficient, and lift/drag ratio are calculated and analyzed.

3. Literature Survey Sl. No AUTHOR NAME TITLE YEAR OF PUBLICATION FINDINGS 1. Erwin et al . Creating and Simulating Turbulence Generation on NACA S1046 Airfoil with CFD Software 2024 Use of turbulators to improve aerodynamic efficiency Placing turbulators at 40-50% of the chord length delays flow separation Results in increases the lift-to-drag ratio and improves blade performance . 2. Samuel et al. CFD Simulation of NACA 2412 airfoil with new cavity shapes 2022 Design keeps the airflow attached to the airfoil beyond 0.25 of the chord length even at higher angles of attack, preventing premature flow separation Results in a higher maximum lift-to-drag ratio (L/D)max​. 3. Brown et al. Evaluating the Influence of Mesh Refinement on CFD Simulations of NACA 4412 Airfoils . 2021 Finer & adaptive meshes improved the resolution of flow features, particularly in regions of high gradient changes like the leading and trailing edges of airfoil.

4. SL.NO AUTHOR NAME TITLE YEAR OF PUBLICATION FINDINGS 4 Bashir et al. CFD Analysis of the NACA 0018 airfoil using different turbulence models 2020 The SST k-omega model provides the most accurate lift coefficient predictions at low angles of attack. The flow separation regions and reattachment locations can be predicted by the Transition k-kl- ω model model . 5. Brown et al. Computational Fluid Dynamics analysis of Cambered/Non-Cambered Airfoils at Low Reynolds Numbers 2018 Cambered airfoils generate higher lift at low speeds compared to symmetric airfoils. Optimized for low-speed conditions, crucial for UAVs and small wind turbines .

5. Research Gap There is a lack of comprehensive studies that investigate the aerodynamic performance of the NACA 4412 airfoil across a broader range of angles of attack and Reynolds numbers, particularly at higher values that are relevant for larger-scale applications or extreme operating conditions. There is a need for a detailed analysis of the NACA 4412 airfoil’s behavior at high angles of attack, where non-linear aerodynamic effects become prominent. Understanding these effects is critical for optimizing performance and avoiding issues like stall in real-world applications. The specific implications of varying the angle of attack and Reynolds number on the NACA 4412 airfoil’s performance in targeted applications (e.g., large-scale wind turbines, high-speed drones) are underexplored. This gap is important for tailoring airfoil designs to meet the unique demands of these applications. There is a need for experimental validation of CFD results, particularly at higher angles of attack and Reynolds numbers, to ensure the accuracy and reliability of the simulations under a wide range of conditions.

6. Objectives of the Study: Evaluate Airfoil Efficiency: To Analyze the aerodynamic performance of the NACA 4412 airfoil profile in wind turbine applications by studying the effects of different angles of attack Simulation Setup: To Conduct Computational Fluid Dynamics (CFD) simulations for angles of attack ranging from 0° to 45°, with 3° increments, to assess performance at high Reynolds numbers. Analyze Aerodynamic Parameters: Static Pressure and Velocity Distributions: Assess how these parameters vary with changes in the angle of attack. Coefficient of Lift (Cl) and Drag (Cd): Calculate and plot these coefficients to understand their relationship with the angle of attack. Lift/Drag Ratio: Determine how the lift/drag ratio changes with varying angles of attack. Identify Optimal Performance: Determine the angle of attack that provides the highest aerodynamic efficiency for the NACA 4412 airfoil.