cfd-mesh-generationlisted

# CFD Mesh Generation (aerodynamics/cfd/cfd-mesh-generation) Use when the task is CFD mesh generation for an aerospace flow case: choosing the grid type, sizing the near-wall spacing from a y plus target, building boundary-layer prism layers, checking cell quality, sizing the far-field domain, or planning refinement. ## Domain quick reference - Grid types: a structured grid is hexahedral with implicit point ordering, efficient for simple geometries such as airfoil sections, cascades, and ducts; an unstructured grid of tetrahedra or polyhedra fits complex geometries such as a full aircraft; a hybrid grid stacks prism layers on the walls and fills the rest with unstructured cells, the standard for wall-bounded external aerodynamics. - Near-wall resolution: the first cell height comes from the dimensionless wall distance y+ = y * u_tau / nu, so y = y+ * nu / u_tau; u_tau = v_inf * sqrt(cf / 2) follows from the skin friction coefficient. A target y+ near 1 resolves the viscous sublayer, values up to about 30 blend wall treatment, and wall functions tolerate y+ up to about 300. - Boundary-layer prism layers grow the first cell outward with a geometric growth ratio, commonly 1.1 to 1.3, until the boundary-layer thickness is covered; the layer count follows the geometric series sum h1 * (r^n - 1) / (r - 1). - Cell quality metrics: skewness near 0 is good and above about 0.9 is bad, the orthogonality angle should stay above about 20 degrees, and the