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Which risk escalates as a high-bypass turbofan engine nacelle approaches Mach 1?

A)Increased shock-wave-induced boundary layer separation
B)Elevated turbine blade thermal creep rate
C)Augmented fuel injector coking formation
D)Worsened compressor blade flutter instability

💡 Explanation

Boundary layer separation risk escalates because shock waves form due to increased air density from reaching equivalent speeds. Adverse pressure gradients induce boundary layer separation, stalling flow; therefore boundary layer separation increases, rather than temperature effects inside the engine.

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