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Which consequence results when supersonic airflow undergoes shock-induced stall?

A)Boundary layer turbulence significantly increases drag
B)Skin friction drag decreases noticeably
C)Lift coefficient linearly decreases gradually
D)Overall pressure reduces behind control surfaces

💡 Explanation

Separation increases drag because adverse pressure gradients instigate boundary layer transition to turbulence via the adverse pressure gradient mechanism; therefore increased skin friction drag is expected rather than a decreasing factor, given the stall and the pressure changes.

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