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Which flow regime develops around airplane wings when viscous effects contribute significantly to the Bernoulli equation?

A)Exceeding critical Mach number locally
B)Boundary layer forms near surface
C)Symmetric laminar pressure distribution result
D)Minimized parasitic aerodynamic turbulence onset

💡 Explanation

A boundary layer forms because fluid viscosity reduces kinetic energy near a surface, impacting pressure calculations using Bernoulli's equation; therefore, layers form rather than the ideal inviscid flow predicted is incorrect because it neglects surface friction.

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