laminar-far-wakelisted

Use when you must compute the two-dimensional laminar far-wake velocity-defect profile and drag downstream of a thin flat plate or slender body at zero incidence, the Goldstein 1933 similarity wake: evaluate the Gaussian cross-stream velocity-defect profile with the spread parameter U/(4*nu*x), the centerline-defect decay as x^-1/2 and the wake half-width growth as x^1/2 downstream of the trailing edge, integrate the momentum deficit across the wake with the wake-momentum-integral drag identity D = rho*U*integral u1 dy to recover the plate drag, and link the far-wake traverse to the laminar Blasius trailing-edge momentum state with the 0.664 constant. Produces the wake velocity-defect and recovered-velocity profiles, the decay and spreading laws and the wake-survey drag in SI units that anchor laminar wake diagnostics and drag checks. Trigger: laminar-far-wake, far-wake-velocity-defect, wake-momentum-integral, velocity-defect-profile, wake-survey-drag.
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# Laminar Far Wake (aerodynamics/boundary-layer/laminar-far-wake) Use when you must compute the two-dimensional incompressible laminar far wake downstream of a thin flat plate at zero incidence, the Goldstein (1933) similarity wake that the attached laminar boundary layers shed from the trailing edge, in the form Schlichting Boundary-Layer Theory (wakes and free-shear-layers chapter, wake behind a flat plate) and White Viscous Fluid Flow (laminar free shear layers, plane wake defect solution) present it. This leaf is the eighth member of the boundary-layer pack and owns the downstream free-shear wake region that every attached-layer sibling stops short of: boundary-layer-theory stops at the plate surface quantities and the transition, separation and unsteady siblings never leave the attached layer. Far downstream of the trailing edge the small velocity defect u1 = U - u collapses onto a Gaussian similarity profile whose cross-stream integral conserves the momentum deficit, and the wake-momentum-integral identity D = rho*U*integral u1 dy is the closed-form basis of wake-survey drag measurement. It does not do attached flat-plate boundary-layer thickness or skin-friction estimation on the surface, transition or separation traverses, creeping Stokes sphere flow, unsteady plate Stokes layers, the wind-tunnel solid-blockage and wake-blockage corrections, or turbulent, axisymmetric, compressible and near-wake flows: incompressible constant-property laminar flow only, small defect