The term c_l, or lift coefficient, is a dimensionless number that represents the lift characteristics of an airfoil at a given angle of attack. It is a crucial parameter in aerodynamics, as it quantifies the lift generated by an airfoil compared to the dynamic pressure of the fluid flow around it. A higher c_l indicates that the airfoil can generate more lift for a given speed and fluid density, which is essential for understanding how various design changes affect aircraft performance.
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