Prandtl’s lifting line equation for a general wing is given by where U_∞ is the free-stream velocity, α is the angle of attack, y₀ is the spanwise location, α_L=0(y₀) gives the spanwise variation of zero-lift angle, c is the chord, b is the span, and Γ(y₀) gives the spanwise variation of circulation.
Given that , the corresponding lift curve-slope is
^∂C_L/_∂α is