stagnation-flow-boundary-layerlisted

# Stagnation-flow boundary layer (aerodynamics/boundary-layer/stagnation-flow-boundary-layer) The laminar boundary layer at a low-speed stagnation point or leading edge (spinner tip, radome nose, wing or fin leading edge) is an attachment-line flow: the inviscid surface speed rises linearly with arc length s from the attachment point, u_e = a * s, and the layer obeys the Hiemenz (2-D) or Homann (axisymmetric) exact similarity solution. This leaf sizes that layer with a deterministic closed-form core: the potential-flow stagnation velocity gradient a from the body radius and freestream speed, the constant 99-percent laminar boundary-layer thickness delta = 2.4 sqrt(nu / a) that does not grow along the attachment region, the wall shear tau_w = mu u_inf sqrt(a / nu) fpp with the classical similarity wall-shear constant fpp (1.2326 Hiemenz, 1.3119 Homann), and the skin-friction coefficient Cf = tau_w / (0.5 rho u_inf^2), plus the swept-edge crossflow treatment for infinite yawed cylinders. The full similarity ODEs are NOT integrated; only their classical constants enter, so every function is pure stdlib, offline and reproducible. This is the low-speed laminar momentum boundary layer only: heat transfer is out of scope. It pairs with boundary-layer-theory (smooth-surface layer sizing away from the attachment line), boundary-layer-transition and boundary-layer-separation (streamwise layer evolution), and aerodynamic-heating (stagnation convective heating at high speed). ## Domain