Comprehensive high-yield formula reference for Incompressible Flow, Thin Airfoil Theory, and Supersonic Shocks.
C_L = 2π (α - α_L=0), dC_L/dα = 2π rad⁻¹ ≈ 0.11 deg⁻¹
C_{D,i} = C_L² / (π e AR), AR = b² / S
T₀/T = 1 + ((γ-1)/2) M², p₀/p = (1 + ((γ-1)/2) M²)^(γ/(γ-1))
M₂² = (2 + (γ-1) M₁²) / (2γ M₁² - (γ-1))