Shock stall is:

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Shock stall is:

Shock stall is:

Options:

separation of the flow at the trailing edge of the wing at high Mach Numbers

separation of the boundary layer behind the shock wave

separation of the flow behind the bow wave

Related questions

1) At higher altitudes, the stall speed (IAS):

2) Shock stall is:

3) The critical angle of attack:

4) Which of the following will reduce induced drag?

5) Which one of the following statements about the lift-to-drag ratio in straight and level flight is correct?