In the transonic range lift will decrease at the shock stall due to the

Question

Question ATPL - Airline Transport Pilot license - Principles of Flight

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Separation of the boundary layer at the shock waves.

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Attachment of the shock wave on the trailing edge of the wing.

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First appearance of a shock wave at the upper side of the wing.

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Appearance of the bow wave.

Id 379 - ATPL - In the transonic range lift will decrease at the shock stall due to the