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Which outcome occurs when an airplane wing's angle of attack increases beyond its critical value?

A)Pressure rapidly increases at wingtip
B)Flow separation leads to stall
C)Laminar boundary transitions to turbulent
D)Lift coefficient maintains optimal values

💡 Explanation

Flow separation leads to stall when exceeding AoA because the adverse pressure gradient overcomes the fluid's inertia per the Bernoulli principle; therefore stall happens rather than increased lift because kinetic energy decreases and viscous effects dominate.

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