![]() The experimental results showed that as the angle of attack increased, the separation and the transition points moved towards the leading edge at all Reynolds numbers. Velocity measurements at different points over the aerofoil were carried out by using a hot-wire anemometer, and oil flow visualization method was used to photograph the surface flow patterns. Moreover, time-dependant lift and drag forces and pitch moment of the aerofoil were obtained by using an external three-component load-cell system. For this investigation, pressure distributions over the aerofoil were measured using a system including a pitot-static tube, a scanivalve unit and a pressure transducer. This study is a detailed experimental investigation on aerodynamics of a NACA2415 aerofoil by varying angle of attack from −12° to 20° at low Reynolds number flight regimes (0.5 × 105 to 3 × 105). A high value of Reynold’s Number will be taken in the scale 106. The Reynolds Number for each simulation will be the same for uniformity in the experiment. The main purpose of this is to find which of the 3 airfoils is the best based on Cd and Cl values for different attack angles. Four different pitch angles were used: 0°, 2°, 4°, 8° to best replicate real-life applications. ![]() ![]() The airfoils examined are made using coordinates derived from the NACA 4-digit series. This paper aims to find the advantages and disadvantages of the 3 different airfoils. The airfoils were designed using NACA guidelines and compared. Airfoil design upholds great importance in modern-day design in aeronautics. Codes have been fed into the MATLAB software to generate the required coordinates. ANSYS Fluent offers us a platform to make simulations. In this study, the comparison between symmetric, anti-symmetric, and semi symmetric airfoil characteristics are made using ANSYS Fluent. Through this paper, the intention is to find out the best airfoil which can be applied for use. Hence to find the best aerodynamic property, we will study the 3 types of airfoils. Extensive research in the maximum L/D ratio is crucial as faster travel is the need of the hour for developing faster and more efficient aircraft, for the military as well as transportation purposes. Airfoils are the cross-section of the wing or blade.
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