panel-methodlisted

Use when the task is panel method setup, source or doublet panels, Neumann or Dirichlet boundary conditions, Kutta condition enforcement, pressure distribution on an airfoil or fuselage, or potential flow over 3D bodies. Compute the surface pressure distribution and force coefficients for an airfoil or body in incompressible potential flow with a panel method: build panel geometry from a closed point list, assemble the source panel influence matrix for the Neumann boundary condition, assemble the doublet panel influence matrix for the Dirichlet boundary condition, solve the linear system, evaluate the surface velocity and pressure coefficient, integrate pressure for lift and drag, and apply the Kutta condition to fix trailing-edge circulation. Trigger: panel method, source panel, doublet panel, kutta condition, neumann boundary condition, dirichlet boundary condition, pressure coefficient, potential flow, 3d body.
ashfordeOU/aero-agent-skills · ★ 0 · AI & Automation · score 78

Install: claude install-skill ashfordeOU/aero-agent-skills

# Surface Panel Method (aerodynamics/cfd/panel-method) Use when the task is a surface panel method for incompressible potential flow: discretizing an airfoil or body into source or doublet panels, applying the Neumann or Dirichlet boundary condition, enforcing the Kutta condition, or computing the pressure distribution and force coefficients. ## Domain quick reference - Panel methods replace the body surface with flat panels carrying constant-strength singularities. Source panels model thickness and non-lifting bodies; doublet panels (or vortex panels) model lifting surfaces; the singularity strengths are the unknowns of a linear system assembled from influence coefficients. - Neumann boundary condition (source panel method): the total velocity normal to the surface is zero at each control point (panel midpoint), sum_j A_ij sigma_j = -(V_inf dot n_i), with the source self-influence A_ii = 1/2. The source panel method reproduces the analytic cylinder pressure coefficient Cp = 1 - 4 sin^2(theta) to machine precision for an inscribed polygon. - Dirichlet boundary condition (doublet panel method): the interior velocity potential is zero at each control point, sum_j D_ij mu_j = -phi_inf_i with D_ii = 1/2. The doublet strength equals the surface velocity potential, so the surface velocity is the surface derivative of the doublet distribution. - Kutta condition: for a lifting body with a sharp trailing edge, the tangential velocities on the upper and l