Abstract
Understanding the aerodynamic behaviour of an airfoil is crucial for evaluating its performance in generating lift and drag. In this study, the aerodynamic performance of the Whitcomb Integral Supercritical Airfoil is analysed across a range of angles of attack—specifically, 2°, 4°, 6°, 8°, and 10°—under sonic conditions. The primary objective is to investigate and characterize the lift and drag properties exhibited by the airfoil at these various angles of attack. This analysis will provide insights into how the airfoil performs in terms of efficiency and stability at sonic speeds.
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