In practice, an inviscid flow is an laminar boundary layer.
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As the flow continues back from the leading edge, the laminar boundary layer increases in thickness.
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Turbulent boundary layers tend to be able to sustain an adverse pressure gradient better than an equivalent laminar boundary layer.
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In contrast, the separation resistance of a laminar boundary layer is independent of Reynolds number a somewhat counterintuitive fact.
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As the pressure begins to recover over the rear part of the wing chord, a laminar boundary layer will tend to separate from the surface.
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However, the same velocity profile which gives the laminar boundary layer its low skin friction also causes it to be badly affected by adverse pressure gradients.
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A common spoiler diffuses air by increasing amounts of turbulence flowing over the shape, " spoiling " the laminar flow and providing a cushion for the laminar boundary layer.
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*H . Schuh, On asymptotic solutions for the heat transfer at varying wall temperatures in a laminar boundary layer with Hartree s velocity profile, J . Aero.
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A consequence of the turbulent boundary layer is increased skin friction relative to a laminar boundary layer, but this is very small compared to the increase in drag associated with separation.
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Unlike the laminar boundary layer equations, the presence of two regimes governed by different sets of flow scales ( i . e . the inner and outer scaling ) has made finding a universal similarity solution for the turbulent boundary layer difficult and controversial.
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