Coefficient of lift for symmetric aerofoil Calculator

The coefficient of lift (CL) for a symmetric airfoil is a dimensionless parameter used in aerodynamics to quantify the lift generated by the airfoil when it is placed in a flow of air. For a symmetric airfoil, the upper and lower surfaces have the same shape, resulting in zero camber (i.e., the mean camber line is a straight line). Due to this symmetry, the coefficient of lift for a symmetric airfoil is typically zero at zero angle of attack (α = 0°). This means that when the angle of attack is zero, the symmetric airfoil produces no lift, and its lift coefficient is zero. 

• CL is the coefficient of lift (dimensionless).
• a is the lift slope or lift-curve slope of the airfoil.
• α is the angle of attack of the airfoil (in radians).