vortex-lattice-methodlisted

# Vortex Lattice Method (aerodynamics/cfd/vortex-lattice-method) Use when the task is computing wing spanwise loading with the horseshoe vortex lattice method: panel geometry, influence coefficients, circulation solution, and the derived lift and induced drag. ## Domain quick reference - The half wing is divided into spanwise panels; each panel carries a horseshoe vortex whose bound segment sits on the quarter chord and whose trailing legs run downstream. - The root-side leg of the root panel is dropped, the mirror-image cancellation of the half-wing model. - The no-penetration condition at the three-quarter chord control points gives a linear system in the panel circulations. - The spanwise lift distribution follows from the Kutta-Joukowski law per panel; the downwash angles at the bound vortices give the induced drag by the near-field estimate. - Near-square panels (spanwise width close to the local chord) give the cleanest solutions; the classic collocation converges to the Prandtl lifting-line result for straight wings. ## Workflow 1. Build the panel lattice with build_wing (span, root and tip chord, panel count). 2. Assemble the influence coefficient matrix with influence_matrix. 3. Solve for the panel circulations with solve_circulations. 4. Derive per-panel lift, downwash angles, and induced drag with lift_distribution, downwash_angles, and induced_drag_coefficient. 5. Report the lift coefficient, induced drag coefficient, and span effi